X-Planes: Lockheed Martin X-35
Filed under: aerospace, history, engineering
The Lockheed Martin X-35 won, which makes it the only aircraft in this series so far whose demonstrator became a production programme, and it won partly on one flight. On 20 July 2001 the X-35B took off in a few hundred feet, climbed to twenty-five thousand feet, accelerated past the speed of sound in level flight, returned to the field and landed vertically. No aircraft had ever done those three things in one sortie, the rival demonstrator could not, and the contract followed three months later. This is the thirty-sixth article in the X-Planes series, following the X-1, the X-2, the X-3, the X-4, the X-5, the X-6, the X-7, the X-8, the X-9, the X-10, the X-11, the X-12, the X-13, the X-14, the X-15, the X-16, the X-17, the X-18, the X-19, the X-20, the X-21, the X-22, the X-23, the X-24, the X-25, the X-26, the X-27, the X-28, the X-29, the X-30, the X-31, the X-32, the X-33, and the X-34.
That sortie is called Mission X, the most famous single flight any aircraft in this series ever made. A flight that famous invites one question, the question can be answered, and this article exists to answer it. What did it establish?
The Research Question
The Sortie Has a Reputation and the Reputation Is Doing Work
The short version, repeated in almost every account, is that the X-35B did in one flight what the X-32 could not do at all, that the rival had to be physically reconfigured between the hovering and supersonic parts of its envelope, and that the fly-off was therefore decided by a capability one team had and the other did not. The rival’s own record bears out the middle clause, since Boeing demonstrated hovering and supersonic flight in separate configurations.
Every clause of that is true and the conclusion still does not follow from it, because the flight was not the experiment. A demonstration that three regimes can be flown in sequence is a demonstration about sequencing. Whether sequencing was the hard part is a separate question. Nobody asks it, because the answer feels obvious and is not.
What This Article Will Not Do
The previous article on the losing side of this competition already made the argument that neither demonstrator was the aircraft being bought, and made it at length. The X-32 and the X-35 were concept demonstrators and not fighter prototypes, and the machines that flew in 2000 and 2001 differed from the production aircraft in structure, in systems, in weight and in purpose. That construct-validity argument is correct and has been made. It will not be remade here.
What remains is a different question, the winner’s. Granting that the demonstrator was a demonstrator, what did its most celebrated flight actually demonstrate?
The Question, Stated So That It Can Be Answered Wrongly
A sortie that performs three manoeuvres in sequence tests something the same three manoeuvres flown on three separate days do not, if and only if the three place demands on the same hardware that interfere. If they do interfere, sequencing them is an existence proof and the flight is evidence. If they do not, sequencing them is scheduling and the flight is a display.
So the keystone of this article is an answerable coupling question. For each of the three events, and for the transitions between them, the article asks what physical quantity was scarce, and computes it. It does not reach the answer the reputation implies, and a later section states the case against its answer openly.
A preview, because a reader is entitled to know where an argument is going. Two of the three events turn out to have been cheap, one of them very cheap indeed, and the expensive thing is not one of the three. It is the conversion between modes, which is not in the name of the trick. Worse for the reputation, and central to the argument, the first in-flight conversion had already been flown eleven days earlier, on a sortie that also went faster than Mission X did.
Programme Origin
What Was Being Bought
The Joint Strike Fighter programme sought a single airframe family for three services and two navies, with a conventional variant, a carrier variant and a short-takeoff and vertical-landing variant sharing enough structure and systems to be affordable. The short-takeoff and vertical-landing requirement constrains everything else, because it demands that an aircraft otherwise sized for supersonic combat also hover, and hovering is the most thrust-hungry thing an aeroplane can do.
The competition ran as a fly-off between two concept demonstrator teams. Each built and flew aircraft covering the three variants, and each demonstrated a different answer to the hovering problem. Neither team started from nothing. The technology base both drew on had been accumulating for four decades, a great deal of it in reports of the National Aeronautics and Space Administration and its predecessor, and most of the period literature this article cites comes from that base, not from the competition itself.
The Invention
The X-35’s answer is due to Paul Bevilaqua and Paul Shumpert at the Lockheed Skunk Works, who set it out in their patent for a propulsion system for a vertical and short takeoff and landing aircraft, granted in 1993. The inventor described the cycle himself in a 1996 paper on dual cycle operation of the shaft driven lift fan and gave the programme’s own account of its origins in the 2009 Wright Brothers Lecture, the genesis of the F-35, and in a companion paper on inventing it. Those are the primary sources for this architecture and the article leans on them.
The idea is unusual enough to state in one sentence. Instead of pointing the engine’s own exhaust downward, take mechanical power off the engine’s shaft, run it forward through a clutch and a bevel gearbox, and use it to drive a separate fan that blows cold air straight down.
Almost every reader’s first reaction is that this is a worse deal, because the fan’s thrust has to come out of the engine’s thrust and a shaft cannot create energy. The reaction is correct about the energy and wrong about the thrust, for a reason given by the most important relation in this article.
One detail of the inventor’s record shows what the fan replaced. Bevilaqua spent the preceding fifteen years on thrust-augmenting ejectors, publishing a lifting surface theory for them in 1977, an evaluation of hypermixing in 1974 and two reviews of advances in ejector thrust augmentation in the 1980s. The ejector is the other way of adding mass flow to a lift system, entraining ambient air into a high-velocity primary jet and not driving a fan with a shaft. The man who displaced it had spent much of his earlier career on it.
The Three Aircraft
Two airframes were built. The X-35A flew first, in the conventional configuration, and was then rebuilt as the X-35B by installing the lift system. The X-35C was a separate aircraft with the larger wing and the strengthened structure of the carrier variant. So the aircraft that flew Mission X is the same airframe that had earlier flown as a conventional fighter, which matters later, because it means the conventional and hovering configurations differed by an installation, not by an airframe.
Sizing From First Principles
The Relation That Makes a Fan Worth Carrying
The relation is the one the X-32 article derives. A jet that accelerates a mass flow $\dot{m}$ from rest to a velocity $v$ produces a thrust and carries away a kinetic power,
\[T = \dot{m} v \qquad \text{and} \qquad P = \tfrac{1}{2} \dot{m} v^{2}\]and eliminating the velocity between them gives the relation that governs every lift system ever built,
\[T = \sqrt{2 P \dot{m}}\]At a fixed power, thrust rises as the square root of the mass flow.
The argument for a lift fan follows from this. A shaft cannot create power, so the fan’s power does come out of the engine. But the fan moves air that the engine never touched, and adding mass flow at fixed power raises thrust. Doubling the mass flow multiplies the thrust by the square root of two even though not one extra joule was spent.
Said the other way round, in the form that makes the design decision obvious, thrust per unit power is inversely proportional to jet velocity. Dividing the two definitions, not eliminating between them,
\[\frac{T}{P} = \frac{\dot{m} v}{\tfrac{1}{2} \dot{m} v^{2}} = \frac{2}{v}\]A hovering aeroplane wants the slowest, fattest jet it can arrange. A supersonic aeroplane wants the opposite. The lift fan exists because those two wants are irreconcilable in one nozzle and reconcilable in two.
The Fan as an Actuator Disc
Three published numbers fix the fan completely and none of them was published in order to. The Rolls-Royce LiftFan is fifty inches in diameter, produces twenty thousand pounds force of thrust, and absorbs twenty-nine thousand shaft horsepower.
Writing $D$ for the diameter, the disc area is
\[A = \frac{\pi D^{2}}{4} = \frac{\pi \times 1.27^{2}}{4} = 1.2668 \ \text{m}^{2}\]Momentum theory treats the fan as a disc across which pressure jumps, with air arriving at rest and leaving at a velocity that is twice the velocity through the disc itself. Writing $v_i$ for the induced velocity at the disc and $\rho$ for sea-level density, thrust and mass flow give
\[T = 2 \rho A v_i^{2} \qquad \Rightarrow \qquad v_i = \sqrt{\frac{T}{2 \rho A}}\]and substituting twenty thousand pounds force, which is 88,964 newtons,
\[v_i = \sqrt{\frac{88{,}964}{2 \times 1.225 \times 1.2668}} = 169.3 \ \text{m/s}\]so the fully developed jet runs at 338.6 metres per second and the mass flow through the disc is
\[\dot{m} = \rho A v_i = 1.225 \times 1.2668 \times 169.3 = 262.7 \ \text{kg/s}\]which is 579.2 pounds per second. The figure is nearly twice the engine core flow that the inversion in a later section recovers. Far from being an accessory, the fan is the larger air handler of the two.
The ideal power such a disc requires is the thrust times the induced velocity,
\[P_{\text{ideal}} = T v_i = 88{,}964 \times 169.3 = 15.06 \ \text{MW}\]against the 21.63 megawatts that twenty-nine thousand shaft horsepower delivers, so the fan’s figure of merit is
\[\mathrm{FM} = \frac{P_{\text{ideal}}}{P_{\text{shaft}}} = \frac{15.06}{21.63} = 0.697\]The previous article recovered the same 0.697 while examining the rival, from the same three numbers, and it belongs to the X-35’s fan and not the X-32’s. A figure of merit near seven tenths is respectable for a heavily loaded fan in a short duct with louvred exit vanes and no time to be elegant.
The same figure follows if the power is taken as the kinetic flux of the fully developed jet, $\tfrac{1}{2} \dot{m} \left(2 v_i\right)^{2} = 2 \dot{m} v_i^{2} = T v_i$, rather than as thrust times induced velocity. The two forms are algebraically identical, so their agreement is a check on the arithmetic and not on the physics.
What the Whole System Multiplies
The lift system’s three published contributors are the fan at twenty thousand pounds force, the three-bearing swivel module at eighteen thousand, and two roll posts at 1,950 pounds force each, giving
\[T_{\text{total}} = 20{,}000 + 18{,}000 + 2 \times 1{,}950 = 41{,}900 \ \text{lbf}\]Those are the figures published for the production LiftSystem, and the 2001 company releases credit the X-35B with nearly 40,000 pounds of vertical force. The total stands against an engine whose dry thrust is twenty-five thousand pounds force. A direct-lift installation of the same engine, which is what the rival built, has that dry thrust and nothing else to hover on. So the shaft-driven arrangement multiplies the available vertical thrust by
\[\frac{41{,}900}{25{,}000} = 1.676\]and it does so without burning any more fuel. The engine is producing the same power either way.
An Unpublished Number Recovered From Three Published Ones
The square-root law shows where that factor came from, and inverting it yields a number the manufacturer never released. If the augmentation is entirely the mass-flow effect, then
\[\frac{T_{\text{total}}}{T_{\text{dry}}} = \sqrt{\frac{\dot{m}_{\text{fan}} + \dot{m}_{\text{core}}}{\dot{m}_{\text{core}}}}\]and solving for the core mass flow, which no source cited here gives,
\[\dot{m}_{\text{core}} = \frac{\dot{m}_{\text{fan}}}{r^{2} - 1} = \frac{579.2}{1.676^{2} - 1} = 320.2 \ \text{lb/s}\]Because no cited source gives an airflow figure for the engine, the inversion cannot be checked against a published value. It is reached from three numbers about thrust and one about a fan, none of which concerns engine airflow.
The figure should not be read for more than it is. The relation assumes the total power is unchanged between the two arrangements, that both jets are ideal, and that the roll posts belong in the numerator, and each of those holds only approximately. It is the core flow the mass-flow mechanism alone would require, and it has not measured the engine.
The Identity the Article Was Already Printing
Momentum theory hands over a second quantity for free, as the X-32 article also shows. The disc loading is thrust over disc area,
\[\frac{T}{A} = \frac{88{,}964}{1.2668} = 70.2 \ \text{kPa}\]and the dynamic pressure in the fully developed jet is
\[q_{\text{jet}} = \tfrac{1}{2} \rho \left(2 v_i\right)^{2} = 2 \rho v_i^{2} = \frac{T}{A}\]so the dynamic pressure the jet puts on the ground is the disc loading, exactly. The equality is an algebraic identity of the ideal disc and holds for any thrust, area and density.
This matters because it converts a propulsion number into a facilities number without any further modelling. A fifty-inch fan making twenty thousand pounds force is also a machine that presses on whatever it is standing over at 70.2 kilopascals, which is about ten pounds per square inch.
Why Cold Matters More Than the Thrust Does
The core stream is a different animal. Its footprint pressure needs the nozzle exit area, which is not published, so it is reached from the mass flow already recovered. For a jet expanded to ambient pressure at exit temperature $T_e$, continuity gives the area and the footprint follows,
\[\rho_e = \frac{p_0}{R T_e} \qquad \text{and} \qquad A_e = \frac{\dot{m}_{\text{core}}}{\rho_e v_e}\]so the pressure the core jet applies to the surface below it is
\[\frac{T_r}{A_e} = \frac{T_r \, \rho_e v_e}{\dot{m}_{\text{core}}}\]At roughly nine hundred kelvin the exit density is 0.3922 kilograms per cubic metre, and taking a dry military exit velocity between 550 and 650 metres per second,
| Assumed exit velocity, m/s | Implied exit area, m² | Footprint pressure, kPa | Ratio to the fan |
|---|---|---|---|
| 550 | 0.6733 | 118.9 | 1.69 |
| 600 | 0.6172 | 129.7 | 1.85 |
| 650 | 0.5697 | 140.5 | 2.00 |
Across the bracket the core jet presses between 1.69 and 2.00 times as hard as the fan does, and it does so at roughly three times the absolute temperature. The fan’s efflux leaves at ambient temperature plus the 46.8 kelvin the compression adds. For the fan pressure ratio $\Pi$ derived under The Torque Nobody Mentions, the isentropic relation gives the exit temperature directly,
\[T_{\text{fan}} = T_0 \, \Pi^{\frac{\gamma - 1}{\gamma}} = 288.15 \times 1.693^{0.2857} = 334.9 \ \text{K}\]The core’s is taken here to leave at about nine hundred kelvin.
So the fan contributes more than thrust. It places a large volume of cold air under the front of the aeroplane, which does two things a hotter, faster jet cannot. It reduces the pressure and temperature the landing surface sees, and it puts a barrier of ambient-temperature air between the hot core efflux and the inlet. The previous article treated hot gas ingestion as the rival’s central difficulty. The X-35’s architecture attacks it at the source.
The Torque Nobody Mentions
The fan is described as two-stage counter-rotating, and the phrase is usually read as a refinement. In fact counter-rotation makes the aircraft controllable.
A single-rotation fan absorbing shaft power $P$ at angular velocity $\omega$ applies a reaction torque to the airframe of
\[Q = \frac{P}{\omega}\]and in a hover there is nothing to react it against except the roll posts, which exist to control the aircraft and not to trim it. The roll posts supply a couple of
\[C = 2 F_{\text{post}} \ell\]where $\ell$ is the distance from the centreline. The fan’s rotational speed is not given in any source cited here, so the relation is inverted, not evaluated. Asking what speed would make the reaction torque consume the entire roll-post couple gives
| Roll-post arm, m | Roll-post couple, N·m | Threshold speed, rpm |
|---|---|---|
| 2.5 | 43,370 | 4,761 |
| 3.0 | 52,044 | 3,968 |
| 3.5 | 60,718 | 3,401 |
| 4.0 | 69,392 | 2,976 |
Every threshold in that table is an ordinary fan speed. An independent estimate of the fan’s actual speed can be built from quantities already computed. The fan raises total pressure by the jet’s dynamic head, giving a pressure ratio of
\[\Pi = \frac{p_0 + q_{\text{jet}}}{p_0} = \frac{101{,}325 + 70{,}229}{101{,}325} = 1.693\]For an isentropic compression the total temperature rise follows from the pressure ratio,
\[\Delta T_0 = T_0 \left(\Pi^{\frac{\gamma - 1}{\gamma}} - 1\right) = 288.15 \times \left(1.693^{0.2857} - 1\right) = 46.8 \ \text{K}\]so the fan does specific work of
\[w = c_p \Delta T_0 = 1004.7 \times 46.8 = 47.0 \ \text{kJ/kg}\]and the air leaves it at 334.9 kelvin, which is the number the ground-environment argument above relies on. Writing $\psi$ for the stage loading coefficient and taking the work as shared between two stages, the blade speed follows from
\[U = \sqrt{\frac{c_p \Delta T_0}{2 \psi}} = \sqrt{\frac{47{,}002}{2 \times 0.40}} = 242.4 \ \text{m/s}\]which is a tip Mach number of 0.712, comfortable for a transonic stage and a check that the assumed loading coefficient is not absurd. The rotational speed is then
\[N = \frac{60 U}{\pi D} = \frac{60 \times 242.4}{\pi \times 1.27} = 3{,}645 \ \text{rpm}\]That estimate sits inside the threshold band and near its middle. The supportable claim is therefore not that counter-rotation saved a stated percentage, but that across every plausible roll-post location a single-rotation fan of this power would have consumed somewhere between three quarters and all of the aircraft’s roll authority merely to stand still. Without counter-rotation there would be no usable control system to improve.
The Clutch and the Halving Identity
The fan is not always running. In conventional flight it is stopped, its doors are closed, and it is carried as dead weight. Entering the hovering mode means opening the doors and engaging a clutch between a running engine and a stationary fan. The article’s thesis holds that this was the hard event, so its cost should be computed exactly.
Consider a source held at a constant angular velocity $\omega_s$ driving an inertia $I$ initially at rest, through a slipping clutch transmitting a torque $Q$ that may vary however it likes. The source does work at a rate $Q \omega_s$. The inertia receives work at a rate $Q \omega$. The difference is destroyed in the clutch. Over the whole engagement the impulse fixes the total,
\[\int Q \, dt = I \omega_s \qquad \Rightarrow \qquad W_{\text{in}} = \omega_s \int Q \, dt = I \omega_s^{2}\]while the inertia ends up holding
\[E_{\text{fan}} = \tfrac{1}{2} I \omega_s^{2}\]so the energy destroyed is the difference,
\[E_{\text{clutch}} = I \omega_s^{2} - \tfrac{1}{2} I \omega_s^{2} = \tfrac{1}{2} I \omega_s^{2}\]Exactly half of the energy drawn from the engine during the engagement is destroyed as heat in the clutch, and nothing about that fraction depends on how the engagement is managed. A slow, gentle engagement destroys exactly as much as a violent one. Integrating the equations of motion under a constant torque, a linearly rising torque and an exponentially decaying torque gives a dissipated fraction of 0.5 in all three cases, as the impulse argument requires.
The magnitude needs the fan’s polar moment of inertia, which is not published, so it is bracketed.
| Assumed inertia, kg·m² | Fan kinetic energy, MJ | Clutch dissipation, MJ | Stored energy as a time, s |
|---|---|---|---|
| 25 | 1.82 | 1.82 | 0.084 |
| 37 | 2.70 | 2.70 | 0.125 |
| 50 | 3.64 | 3.64 | 0.168 |
The last column is the useful one, and the bracket does not weaken it. It is
\[\tau = \frac{E_{\text{fan}}}{P_{\text{shaft}}} = \frac{I \omega_s^{2}}{2 P_{\text{shaft}}}\]the fan’s stored kinetic energy divided by the power it absorbs when running, which has the dimensions of time, and across the bracket it stays under a fifth of a second. The fan stores less than a fifth of a second of its operating power.
The heat has to go somewhere, and the same bracket gives its effect on the clutch. For a plate pack of mass $m_p$ and specific heat $c_p$, an adiabatic engagement raises its temperature by
\[\Delta T_p = \frac{E_{\text{clutch}}}{m_p c_p} = \frac{I \omega_s^{2}}{2 m_p c_p}\]and for an assumed twenty kilograms of carbon at 710 joules per kilogram kelvin that is 128.3, 189.8 and 256.5 kelvin across the three inertias. Those are ordinary friction-material temperatures, which is the first sign that the engagement is thermally modest.
What the Bound Rules Out
The cited sources give no engagement time for the X-35B’s clutch, so the bound is taken for an assumed engagement time $t$ of nine seconds. Combining that time with the rated shaft power gives a bound that assumes nothing about the fan. At most the rated power can flow for at most that time, and at most half of it can be destroyed, so
\[E_{\text{clutch}} \le \tfrac{1}{2} P t = \tfrac{1}{2} \times 21.63 \times 10^{6} \times 9 = 97.3 \ \text{MJ}\]That bound is absurd and its absurdity is the finding. Ninety-seven megajoules deposited into an assumed twenty kilograms of carbon would raise its temperature by about 6,853 kelvin, which is beyond the vaporisation point of anything. The engagement therefore cannot be anywhere near power-limited.
Comparing the bound with the bracket gives the size of the margin. Spreading the bracketed dissipation over the assumed nine seconds and dividing by the bound’s rate, which is half the shaft power, gives
\[\frac{E_{\text{clutch}} / t}{\tfrac{1}{2} P} = \frac{E_{\text{clutch}}}{\tfrac{1}{2} P t} = \frac{1.82}{97.3} = 0.0187 \quad \text{to} \quad \frac{3.64}{97.3} = 0.0374\]across the inertia bracket, so the mean dissipation is between 1.9 and 3.7 percent of the most the shaft could feed into the clutch. The bound exceeds the dissipation across the inertia bracket for any engagement longer than about a third of a second, so the conclusion does not rest on the assumed time. The energy does not set an engagement of that length. If anything in the clutch sets it, the heat does, and that difference explains why a mode change on this aircraft is a scheduled sequence of doors opening, the clutch engaging and the clutch locking, not the flick of a switch.
The Force That Appears the Moment the Fan Engages
The conversion’s largest single effect is a force that most descriptions of this aeroplane do not mention. A lift fan running in forward flight ingests air travelling at the aircraft’s speed and discharges it vertically. All of that horizontal momentum has to be destroyed, and the reaction is a drag force.
Writing $\dot{m}$ for the fan’s mass flow and $V$ for true airspeed,
\[D_{\text{mom}} = \dot{m} V\]which is exact and needs nothing beyond the flow the disc analysis already produced. The same mass flow follows from thrust over jet velocity, since the ideal disc has $T = \dot{m} v_j$ identically.
| Speed, kt | Momentum drag, lbf | As a share of the swivel module’s thrust | As a share of weight |
|---|---|---|---|
| 60 | 1,823 | 10.1 percent | 5.4 percent |
| 80 | 2,431 | 13.5 percent | 7.2 percent |
| 120 | 3,646 | 20.3 percent | 10.7 percent |
| 150 | 4,558 | 25.3 percent | 13.4 percent |
| 180 | 5,469 | 30.4 percent | 16.1 percent |
The X-35B made its first in-flight conversion at 180 knots, and at that speed engaging the fan costs 5,469 pounds force of drag. That is 30.4 percent of everything the rear nozzle can produce, and on its own it would decelerate the aircraft at
\[a = \frac{D_{\text{mom}}}{m} = \frac{24{,}329}{15{,}422} = 1.578 \ \text{m/s}^{2} = 0.1609 \, g\]These figures give quantitative content to the claim that the conversion was the hard event. Nothing about hovering, going supersonic or landing vertically produces a step change of that size. Opening the doors and letting the clutch in does.
Where That Drag Acts
The fan sits ahead of the centre of gravity and its inlet doors are on top of the fuselage, so the momentum drag is a horizontal force applied above and forward of the centre of mass, and it therefore pitches the aircraft as well as decelerating it.
The inlet’s height above the centre of gravity is unpublished, so the relation is solved for the height that would matter. Pitch control in the hover comes from shifting thrust between the fan and the rear nozzle, and an authority of ten percent of the fan’s thrust acting on its moment arm gives
\[M_{\text{avail}} = 0.10 \, T_f x_f = 0.10 \times 88{,}964 \times 3.553 = 31{,}606 \ \text{N m}\]Setting that equal to the momentum-drag moment gives the height at which the two are equal,
\[h^{*} = \frac{M_{\text{avail}}}{D_{\text{mom}}} = \frac{31{,}606}{24{,}329} = 1.299 \ \text{m}\]If the dorsal fan inlet sits roughly a metre above the centre of gravity, which is an estimate and not a published figure, the threshold is not comfortably far away. What can be said is that the momentum drag’s pitching moment is of the same order as the trim authority available to oppose it, which is why a conversion is flown as a scheduled and gradual event rather than as a switch.
The Hover Balance Fixes the Centre of Gravity
In wing-borne flight an aeroplane trims by moving a control surface. In a hover it cannot, because there is no airflow to work against. The only vertical forces are the fan ahead of the centre of gravity and the rear nozzle behind it, and in steady hover their moments must cancel,
\[T_f x_f = T_r x_r\]Both thrusts are fixed by the hardware, so this equation does not determine the trim. It determines where the centre of gravity has to be. Writing $L$ for the separation between the two,
\[\frac{x_f}{L} = \frac{T_r}{T_f + T_r} = \frac{18{,}000}{38{,}000} = 0.4737\]The centre of gravity must sit at 47.37 percent of the distance from the fan to the rear nozzle, and for an assumed separation of 7.5 metres that is 3.553 metres behind the fan and 3.947 metres ahead of the nozzle. The ratio of the two arms is fixed at 0.9 by the ratio of the two thrusts and by nothing else.
How tightly that is fixed is the useful question. Modulating the split in opposite directions moves the balance point across the following band.
| Split modulation | Reachable station, fraction from the fan | Travel |
|---|---|---|
| 2 percent | 0.4637 to 0.4837 | 5.89 inches |
| 5 percent | 0.4488 to 0.4987 | 14.72 inches |
| 10 percent | 0.4241 to 0.5238 | 29.45 inches |
A few percent of thrust split yields a few inches of centre-of-gravity travel. That is a tight band for an aeroplane whose fuel and stores move the centre of gravity by considerably more, and it is a cost of the architecture that does not ease as the aircraft gets lighter, unlike every other margin in this article.
What an Inlet Temperature Rise Costs, in Kelvin
The lift fan is shaft-driven, which means every pound of vertical thrust in this aircraft is ultimately core thrust. The fan has no combustor of its own. So an engine that swallows its own hot exhaust loses the fan and the rear nozzle together, and the ground-environment argument made earlier can now be quantified.
At a fixed corrected operating point the physical mass flow, and with it the thrust, falls as the inverse of inlet total temperature. This relation needs a thrust and a temperature in the same expression, and the article has used $T$ for thrust throughout, so thrust is written $F$ here and only here.
\[\frac{F}{F_{0}} = \frac{T_{\text{amb}}}{T_{\text{amb}} + \Delta T}\]| Inlet rise, K | Thrust retained | Vertical thrust, lbf | Hover margin |
|---|---|---|---|
| 0 | 1.000 | 41,900 | 1.232 |
| 10 | 0.966 | 40,495 | 1.191 |
| 20 | 0.935 | 39,181 | 1.152 |
| 30 | 0.906 | 37,949 | 1.116 |
| 50 | 0.852 | 35,705 | 1.050 |
The losses are 3.354, 6.490, 9.430 and 14.786 percent respectively. Inverting for the rise that consumes the margin entirely gives
\[\Delta T_{\text{crit}} = T_{\text{amb}} \left(\frac{F_{\text{total}}}{W} - 1\right) = 288.15 \times 0.2324 = 66.95 \ \text{K}\]At 34,000 pounds the X-35B could tolerate a 66.95 kelvin inlet temperature rise before it could no longer hold itself up. That single number measures the value of the cold fan. It accounts for the architecture’s choice to place a large volume of ambient air between the hot core efflux and the inlets instead of managing ingestion afterwards, and it converts a comparison with the rival from a matter of adjectives into a matter of kelvin.
The Vehicle
Two airframes covered three configurations. The X-35A flew as a conventional fighter from 24 October 2000, was then rebuilt with the lift system installed, and flew again as the X-35B. The X-35C was a separate aircraft carrying the carrier variant’s larger wing and heavier structure.
The demonstrators were deliberately simpler than the production aircraft. They carried no weapons bays, no radar, no mission systems and no low-observable treatment of the kind the product would need, and they used off-the-shelf components wherever schedule allowed. The X-35A’s published empty weight of 26,500 pounds belongs to a machine built to answer a question, not to fight. The maximum takeoff weight of fifty thousand pounds printed beside it is the figure of the 1998 operational requirement.
Dependent Systems
The Three-Bearing Swivel Module
The rear nozzle redirects the core exhaust downward through a jointed pipe whose three canted bearings, rotated relative to one another, sweep the nozzle through ninety-five degrees in 2.5 seconds, a mean slew rate of
\(\dot{\delta} = \frac{\Delta \delta}{\Delta t} = \frac{95^{\circ}}{2.5 \ \text{s}} = 38.0 \ \text{deg/s}\) The elegance is that a purely rotational mechanism produces a large angular deflection, so the sealing problem is a set of rotating joints rather than a set of sliding ones, at a station carrying the full core efflux.
The number of bearings is not a styling choice, and the geometry fixes the count at three. Take a single joint whose mating plane is inclined at an angle $\beta$ to the duct axis. Rolling one side relative to the other by $\phi$ deflects the downstream axis by $\delta$, where
\[\cos\delta = \cos^{2}\beta + \sin^{2}\beta \cos\phi\]At half a turn it reduces to $\delta = 2\beta$, so one joint can bend the duct by twice its cant angle and no more.
\[\beta_{\text{single}} = \frac{95^{\circ}}{2} = 47.5^{\circ}\]A single bearing would therefore need its mating plane canted at 47.5 degrees, which is an extraordinary angle for a pressure-tight rotating seal carrying the full exhaust of an augmented turbofan. Such a joint would be impractical.
Putting joints in series helps only if their cants alternate, and this condition is not obvious. A numerical search over the roll angles found that two joints canted the same way reach $2\beta$ and no more, because the second can only undo what the first did. Mirror the second joint and the two add to $4\beta$, and three alternating joints reach $6\beta$, which the search confirmed to the grid resolution at a cant of fifteen degrees.
\[\beta_{\text{three}} = \frac{95^{\circ}}{6} = 15.83^{\circ}\]Sixteen degrees is an ordinary cant for a rotating duct joint. So the count of bearings follows from the angle a sealed joint can tolerate, divided into the deflection the aircraft needs. The actual cant angles and the gearing between the three rings are not published, and this article claims only the requirement and leaves the mechanism open.
The Inlet
The inlet is a diverterless supersonic design, replacing the boundary-layer diverter of a conventional installation with a fixed compression surface that pushes the boundary layer sideways. It removes weight, moving parts and radar return at once, and it does so at the cost of being optimised for one region of the envelope rather than adjustable across it. For a demonstrator flown to about Mach 1.2 that cost is invisible, a point to bear in mind when reading the supersonic leg of Mission X.
Roll Posts and Control Power
Bleed from the engine’s fan is ducted to nozzles in each wing, giving 1,950 pounds force each, which is half of the 3,900 pounds force published for the pair combined. In a hover an aeroplane has no aerodynamic control at all, so every axis must be held by thrust modulation. Pitch comes from splitting thrust between the lift fan and the rear nozzle, yaw from vectoring the rear nozzle laterally, and roll from the posts.
The earlier counter-rotation result can be turned from a fraction into something a pilot would feel. The posts supply a couple, and dividing by the roll moment of inertia gives an angular acceleration,
\[\dot{p} = \frac{2 F_{\text{post}} \ell}{I_{xx}}\]The inertia is not published, so it is estimated from a radius of gyration taken as a fraction of span and reported across a bracket. At 0.22 of the span,
\[I_{xx} = m k_x^{2} = 15{,}422 \times 2.213^{2} = 75{,}400 \ \text{kg m}^{2}\]which is 75,400 kilogram metres squared, and with the posts at 3.5 metres from the centreline the couple of 60,718 newton metres gives
\[\dot{p} = \frac{60{,}718}{75{,}400} = 0.805 \ \text{rad/s}^{2} = 46.07 \ \text{deg/s}^{2}\]which is a healthy figure for a hovering aircraft. Across the plausible bracket of radius of gyration and post position it runs from 30.6 to 55.7 degrees per second squared.
Now subtract what a single-rotation fan would have taken. Its reaction torque at the speed estimated above is 56,655 newton metres, which is 93.31 percent of the couple, leaving 4,063 newton metres and
\[\dot{p}_{\text{residual}} = \frac{4{,}063}{75{,}400} = 3.083 \ \text{deg/s}^{2}\]Three degrees per second squared is not a degraded control system. It is not a control system. A pilot holding a hover in a crosswind would have had about one fifteenth of the roll acceleration the aircraft has. That difference is the return on the counter-rotating fan, expressed in the units the handling-qualities literature uses, and it makes a stronger statement than the percentage the earlier section could make.
Structure and the Variant Problem
The three variants share a fuselage cross-section and a great deal of structure, and differ in wing area, in landing gear, and in whether a lift fan occupies the volume immediately behind the cockpit. That shared volume is the hardest constraint in the design, because the conventional and carrier variants carry fuel where the short-takeoff and vertical-landing variant, or STOVL variant, carries a fan, and the airframe has to be the same airframe for the commonality argument to pay. The STOVL variant trades fuel volume for vertical flight systems, and the carrier variant has a larger wing and stronger landing gear.
The size of that constraint can be estimated. The fan bay is at least the swept volume of the fan itself,
\[V = \frac{\pi D^{2}}{4} \ell\]and for the fifty-inch fan over an assumed bay length between 1.2 and 1.6 metres that is 1.52 to 2.03 cubic metres. Filled with fuel at 800 kilograms per cubic metre instead,
\[W_{\text{fuel}} = \rho_f V = 800 \times 1.773 = 1{,}419 \ \text{kg} = 3{,}128 \ \text{lb}\]so the hovering variant gives up roughly three thousand pounds of internal fuel to the fan, running from 2,681 pounds at the short bay to 3,575 at the long one. That is the commonality argument’s bill, paid in range by the variant that can least afford it. The estimate is a lower bound, since the bay must also house doors, the drive shaft and the clutch.
The Flight Test Record
The Precedents
Two aircraft had already solved parts of this problem. The Harrier made vertical landing an operational reality from the late 1960s using a single engine with four rotating nozzles, and it was never supersonic. The Yak-141 was supersonic and hovered, using two dedicated lift engines and a main engine exhausting through a three-bearing swivel nozzle.
That last phrase also describes the X-35’s rear nozzle. Lockheed and Yakovlev entered a partnership in 1991 for further development of the Yak-141, and the resemblance between the two swivel modules is close and widely noted. How much of the X-35’s nozzle descends from that arrangement is disputed and this article does not attempt to settle it, but the concept was not invented at Palmdale and the article would be misleading if it implied otherwise. The X-35 reference credits a 1972 Convair design with pioneering the three-bearing swivel nozzle. The shaft-driven lift fan is the newer idea. The nozzle behind it has a longer history. Even the fan dates as a concept to the mid-1950s, and the X-35B was the first aircraft a shaft-driven lift fan lifted into the sky.
What Actually Flew
| Aircraft | First flight | Flights | Notes |
|---|---|---|---|
| X-35A | 24 October 2000 | 27 in 30 days | Conventional, completed 22 November 2000 |
| X-35C | 16 December 2000 | 73, 58 hours | Carrier variant, completed 11 March 2001 |
| X-35B | 23 June 2001, first vertical | 23 June to 30 July 2001 | Rebuilt from the X-35A |
Lockheed Martin’s report at the end of the campaign gives the X-35B’s totals as 27 vertical landings, 14 short takeoffs, 18 vertical takeoffs, five supersonic flights and five aerial refuellings. A 2008 Lockheed Martin release gives 17 vertical takeoffs for the same campaign, with the same 14 short takeoffs and 27 vertical landings.
One number in the table is disputed, and this article records the disagreement without resolving it. Contemporary programme reporting gives the X-35A 27 flights in thirty days, while a later reference account gives 28 test flights. No conclusion here turns on which is right.
The Eleven Days That Contain the Answer
This section carries the article’s central evidence. Setting the X-35B’s flights out in order, with the first occurrence of each capability marked, does something no summary of Mission X does.
| Date, 2001 | Event | First of its kind for this aircraft |
|---|---|---|
| 23 June | Vertical takeoff, hover, vertical landing at Palmdale | Yes |
| 24 June | First sustained hover | Yes |
| late June | Seventeen vertical takeoffs, hovers and landings completed | No |
| 9 July | In-flight conversion to hovering mode, aerial refuelling, and Mach 1.08, in one sortie | Yes, and this is the hard one |
| 16 July | Short takeoff, wingborne to jet-borne transition, vertical landing | Short takeoff, yes |
| 20 July | Mission X, short takeoff, Mach 1.05, vertical landing | No. Nothing on this sortie was new |
| 26 July | Mission X repeated, then a sixty-knot short takeoff ending in a vertical landing at over 34,000 pounds | No |
| 30 July | Campaign complete |
By 16 July the aircraft had already flown every element of Mission X. It had converted between modes in flight, it had gone supersonic, it had taken off short, it had transitioned from wingborne to jet-borne flight, and it had landed vertically. Lockheed Martin’s programme general manager listed short takeoffs, transitions, hovers, vertical landings and supersonic flight as complete at the time, four days before the famous flight, and the pilot who flew Mission X later wrote that each event had been accomplished on a previous sortie.
And the 9 July sortie went faster than Mission X did. It reached an indicated Mach 1.08 against Mission X’s Mach 1.05, and it did so on the same flight as the aircraft’s first in-flight conversion to hovering mode and an aerial refuelling.
So Mission X contained no manoeuvre the aircraft had not already performed, and it was not the aircraft’s fastest flight. What it contained was the assembly. Assembly is a legitimate thing to demonstrate, but it differs from what the reputation implies.
Comparison With Ground Prediction
The Short Takeoff, Reconstructed
Two short takeoffs are documented well enough to be examined. On 20 July the Mission X takeoff left the ground at about eighty knots, and the pilot’s own account adds that this came after only 200 feet, at which point he vectored the thrust to 60 degrees and the aircraft left the ground. A short takeoff flown on 26 July, on the flight after that day’s Mission X repetition, used approximately five hundred feet of runway and left the ground at about sixty knots, and the same flight ended in a vertical landing at an aircraft weight of more than 34,000 pounds. That aircraft therefore weighed more than 34,000 pounds at takeoff. No Mission X weight is published, and the section headed The Takeoff Did Not Have to Be Short bounds it between 34,197 and 45,697 pounds.
At unstick the weight is carried by two things, and only two. Writing $L$ for wing lift, $T_v$ for whatever the lift system points downward and $W$ for weight, an aircraft leaves the ground once
\[L + T_v \ge W, \qquad L = \tfrac{1}{2} \rho V^{2} S C_L\]The fan and the roll posts point downward whatever the rear nozzle does,
\[T_f = 20{,}000 + 2 \times 1{,}950 = 23{,}900 \ \text{lbf}\]and a rear nozzle of thrust $T_r$ deflected by $\theta$ below the horizontal adds $T_r \sin\theta$. Assuming that the rear nozzle delivers its published 18,000 pounds force at eighty knots, the Mission X vectoring to 60 degrees gives
\[T_v = T_f + T_r \sin\theta = 23{,}900 + 18{,}000 \sin 60^{\circ} = 23{,}900 + 15{,}588 = 39{,}488 \ \text{lbf}\]At eighty knots over 41.81 square metres of wing the dynamic pressure times area is
\[\tfrac{1}{2} \rho V^{2} S = \tfrac{1}{2} \times 1.225 \times 41.156^{2} \times 41.81 = 43{,}376 \ \text{N} = 9{,}751 \ \text{lbf}\]so the lift coefficient the record requires is at most what the heaviest weight in the bracket demands,
\[C_L \ge \frac{W - T_v}{\tfrac{1}{2} \rho V^{2} S} = \frac{45{,}697 - 39{,}488}{9{,}751} = 0.637\]The finding is that the record cannot pin a lift coefficient. At any weight up to 39,488 pounds the vectored lift system alone exceeds the weight and the required coefficient is zero or negative, and at the ceiling of the bracket the wing need supply no more than a coefficient of 0.637. A Mission X unstick at eighty knots with the nozzle at 60 degrees is consistent with a wide range of wing lift, because the lift system was carrying at least 86 percent of the aircraft.
The 26 July takeoff can be read the same way, and it too leaves the coefficient open. At sixty knots
\[\tfrac{1}{2} \rho V^{2} S = \tfrac{1}{2} \times 1.225 \times 30.867^{2} \times 41.81 = 24{,}399 \ \text{N} = 5{,}485 \ \text{lbf}\]and the deflection that balances the weight at unstick is
\[\sin\theta = \frac{W - T_f - C_L \, \tfrac{1}{2} \rho V^{2} S}{T_r}\]which depends on both the unpublished weight and the unknown coefficient,
| Weight, lb | Deflection at $C_L = 0$ | Deflection at $C_L = 0.5$ | Deflection at $C_L = 1.0$ |
|---|---|---|---|
| 34,000, the documented floor for that flight | 34.13 degrees | 24.13 degrees | 14.86 degrees |
| 45,697, the ceiling of the bracket | no balance | no balance | 64.99 degrees |
At the documented floor every entry is inside the swivel module’s ninety-five degrees, so at that weight the lift system could have balanced the aircraft at sixty knots with no help from the wing. At the ceiling of the bracket it could not, because its 41,900 pounds force falls short of the weight even with the nozzle pointing straight down, and the wing must then supply a coefficient of at least 0.692. The record is silent on how far the nozzle moved on 26 July, and the one deflection it does record, the 60 degrees of Mission X, is larger than most of the table requires.
The Conversion Corridor, Read From the Record
The conversion speed does not need the unstick coefficient, because the record answers it directly. On 9 July the aircraft climbed to 9,000 feet and engaged the lift fan at 180 knots, flying conventionally until that moment, so the wing was carrying the whole weight when the fan engaged. Evaluating at sea-level density, as the momentum drag figure also does, which is an assumption, the coefficient the wing was flying at follows from
\[C_L = \frac{W}{\tfrac{1}{2} \rho V^{2} S}, \qquad \tfrac{1}{2} \times 1.225 \times 92.6^{2} \times 41.81 = 219{,}588 \ \text{N} = 49{,}365 \ \text{lbf}\]which for any weight between the 30,697 pound empty weight taken for the bracket and the 45,697 pounds of a full internal fuel load is
\[C_L = \frac{30{,}697}{49{,}365} = 0.622 \quad \text{to} \quad \frac{45{,}697}{49{,}365} = 0.926\]The X-35B made its first in-flight conversion where lift was already free. That is the safest place to engage a lift fan, because a failure of the engagement leaves an aircraft that is already flying. And it is still the point at which the momentum drag computed earlier is at its largest. The conversion was flown where lift was free and drag was most expensive, the right trade though not an obvious one. The speed below which the wing could not have carried the aircraft unaided depends on the wing’s usable lift coefficient, which no source gives, so this article does not state one.
The Ground Roll, and a Figure That Cannot Be Right
The 200 foot figure does not survive the arithmetic. Reaching eighty knots from rest in 200 feet takes a mean acceleration of
\[\bar{a} = \frac{V^{2}}{2 s} = \frac{41.156^{2}}{2 \times 60.96} = 13.89 \ \text{m/s}^{2} = 1.417 \, g\]and even if every pound of the lift system’s published thrust pointed aft, with no drag and no rolling friction, the lightest weight in the bracket allows at most
\[\frac{a_{\max}}{g} = \frac{T_{\text{total}}}{W} = \frac{41{,}900}{34{,}197} = 1.225\]In fact only the rear nozzle points aft during a roll, and its 18,000 pounds force at that weight gives a frictionless, dragless minimum of
\[s_{\min} = \frac{V^{2}}{2 g \, T_r / W} = \frac{41.156^{2}}{2 \times 9.80665 \times 0.5264} = 164.1 \ \text{m} = 538.3 \ \text{ft}\]So the 200 feet and the eighty knots cannot both describe a roll from brake release. The account was written for a general readership after the event, and one of the two figures, or what the distance was measured from, must differ from what the printed sentence says. The 2001 press release figure for that flight is the speed alone. The company’s 2019 account gives a 450-foot takeoff, which is also shorter than the 538 foot minimum, and this article relies on the speed.
The 26 July roll does close, and it leaves a margin. Taking the nozzle as pointing aft during the roll and moving only at unstick, which is what the Mission X account describes and is an assumption for 26 July, the equation of motion is
\[m \frac{dV}{dt} = T_r \cos\theta - \mu \left(W - T_v\right) - \tfrac{1}{2} \rho V^{2} S C_{D_0}, \qquad \theta = 0\]Writing $A$ for the constant part of the acceleration and $B$ for the quadratic drag coefficient divided by mass, this integrates in closed form to
\[s = \frac{1}{2B} \ln\!\left(\frac{A}{A - B V^{2}}\right)\]and at the 34,000 pound floor for that flight, substituting $A = 5.104$ and $B = 4.151 \times 10^{-5}$,
\[s_{\min} = 93.69 \ \text{m} = 307.4 \ \text{ft}\]The quoted roll $s_q$ needs a mean acceleration of
\[\bar{a} = \frac{V^{2}}{2 s_q} = \frac{30.867^{2}}{2 \times 152.4} = 3.126 \ \text{m/s}^{2} = 0.3187 \, g\]against the acceleration available, which is $A$ less the drag term evaluated at half the squared unstick speed,
\[a_{\text{avail}} = A - \tfrac{1}{2} B V^{2}\]Across the weight bracket for that flight,
| Weight, lb | $A$, m/s² | $B$, 1/m | Minimum roll, ft | Quoted over minimum | Available, $g$ | Share used |
|---|---|---|---|---|---|---|
| 34,000 | 5.104 | 4.151 × 10⁻⁵ | 307.4 | 1.627 | 0.518 | 0.615 |
| 45,697 | 3.722 | 3.088 × 10⁻⁵ | 421.5 | 1.186 | 0.378 | 0.843 |
where the share used is $\bar{a} / a_{\text{avail}}$. The quoted five hundred feet is longer than the minimum at every weight in the bracket, by a factor between 1.186 and 1.627, so between 61.5 and 84.3 percent of the available horizontal thrust appears in the quoted distance. Thrust build-up from brake release accounts for part of the gap.
Acceleration was not scarce. An aircraft that can reach its unstick speed in between 307 and 422 feet and takes 500 is not straining, and there is no reason it should have been strained, because of the number in the next paragraph.
The Takeoff Did Not Have to Be Short
Total vertical thrust is 41,900 pounds force, and the largest weight it can hold up follows immediately,
\[W_{\max} = \frac{T_{\text{total}}}{g} = \frac{186{,}381}{9.80665} = 19{,}006 \ \text{kg} = 41{,}900 \ \text{lb}\]The numerical coincidence between the weight limit in pounds and the thrust in pounds force is an artefact of the unit system rather than a result. At the 34,000 pounds the aircraft is documented to have weighed on the 26 July flight, the margin is
\[\frac{T_{\text{total}}}{W} = \frac{41{,}900}{34{,}000} = 1.232\]so at that weight the X-35B could have taken off vertically. It had already done so seventeen times in late June.
No takeoff weight or fuel state for Mission X itself has been published. The pilot’s own account records that the sortie followed a familiarisation flight and a hot refuelling, and that by the end fuel and time were short enough that the last set of test points was dropped. The weight is therefore bounded rather than known. Its floor is the empty weight plus the fuel the sortie burned, since the aircraft must have carried at least that much, and its ceiling is the empty weight plus the 15,000 pounds of internal fuel the aircraft could hold. Assuming that burn to be 3,500 pounds, and neglecting the pilot and the test instrumentation, both of which add to every weight in the bracket,
\[W_{\text{TO}} = W_{\text{empty}} + W_{\text{fuel}}, \qquad 30{,}697 + 3{,}500 = 34{,}197 \ \le \ W_{\text{TO}} \ \le \ 30{,}697 + 15{,}000 = 45{,}697 \ \text{lb}\]The empty weight in that bracket is the least certain input, and no weighing record for the X-35B is public. The X-35 reference gives 26,500 pounds for the X-35A and 30,697 pounds for the X-35B. Another compilation gives about 22,000 pounds for the X-35A and about 23,500 pounds for the X-35B. The bracket takes the 30,697 pounds. Its excess of 4,197 pounds over the X-35A figure lies within five percent of the 4,000 pounds that the lift fan installation was reported in 1998 to add to the Lockheed Martin design. The compilation’s excess is 1,500 pounds, and its X-35A figure equals the dry weight of about 22,000 pounds in that year’s operational requirement, which suggests a requirement figure in place of a measured one. The lower figure would move both ends of the bracket down by 7,197 pounds, to between 27,000 and 38,500 pounds. The internal fuel figure also matches that requirement, which asked for 15,000 pounds or more, so the ceiling may describe the production design’s tanks more closely than the demonstrator’s.
At the ceiling the margin is
\[\frac{T_{\text{total}}}{W_{\text{TO}}} = \frac{41{,}900}{45{,}697} = 0.9169\]which is below unity, so at full internal fuel the X-35B could not have taken off vertically at all. Vertical takeoff needs a weight below 41,900 pounds, which is a fuel load below 11,203 pounds, or about three quarters of the internal capacity, before the 3.354 percent of thrust that the corrected-flow relation above removes for a ten kelvin inlet temperature rise is counted. Taken at the round 40,000 pounds of vertical force that the 2001 releases credit to the X-35B, the limit falls to a fuel load of 9,303 pounds, or 62 percent of capacity, and the margin at 34,000 pounds falls to 1.176. Under the lower compilation empty weight the margin at full internal fuel would instead be 1.088. Every X-35B vertical takeoff, hover and landing was also flown at 2,500 feet elevation in temperatures up to 94 degrees Fahrenheit, conditions that the sea-level standard thrust does not describe.
So the claim holds only in a narrowed form. At 34,000 pounds, and at any Mission X takeoff weight with well under three quarters of the internal fuel, the X-35B could have taken off vertically, and the short takeoff demonstrated a technique rather than relieving a constraint. On the 30,697 pound empty weight, above about three quarters the weight exceeds the sea-level vertical thrust, short of it the margin is smaller than what temperature and elevation plausibly consume, and the fuel Mission X carried has never been released. A short takeoff exists in the operational requirement because the aeroplane that matters will be heavier than its vertical thrust, and will need wing lift to get airborne with a useful load. The record does not show the demonstrator in that condition on 20 July, and it does not exclude it.
The Supersonic Leg Was Thermally Free
Mission X reached Mach 1.05 at twenty-five thousand feet, and the conditions there follow from the standard atmosphere. Below the tropopause the temperature falls linearly and the hydrostatic equation integrates to a power law,
\[T = T_{\text{SL}} - Lh \qquad \text{and} \qquad p = p_{\text{SL}} \left(\frac{T}{T_{\text{SL}}}\right)^{\frac{g_0}{RL}}\]whose exponent is
\[\frac{g_0}{RL} = \frac{9.80665}{287.05 \times 0.0065} = 5.2559\]At 7,620 metres this gives a static temperature of 238.62 kelvin and a pressure of 37,601 pascals, so the density and speed of sound are
\[\rho = \frac{p}{RT} = 0.5489 \ \text{kg/m}^{3} \qquad \text{and} \qquad a = \sqrt{\gamma R T} = 309.7 \ \text{m/s}\]and the aircraft was travelling at 325.2 metres per second. The density ratio against sea level is 0.4481, which is the number the thrust available depends on. The stagnation temperature follows from the energy equation,
\[T_0 = T + \frac{V^{2}}{2 c_p} = 238.62 + \frac{325.2^{2}}{2 \times 1004.7} = 291.2 \ \text{K}\]which is 18.1 degrees Celsius. The hottest air the airframe met during its supersonic dash was 3.1 kelvin warmer than a standard day at sea level.
There was no thermal event. Kinetic heating at low supersonic speed is negligible, and any argument that sequencing a supersonic dash before a vertical landing subjected the lift system to a hot start has no support.
Nor was thrust scarce, and the drag can be built up from its parts rather than taken as one lumped coefficient. The dynamic pressure is
\[q = \tfrac{1}{2} \rho V^{2} = \tfrac{1}{2} \times 0.5489 \times 325.2^{2} = 29{,}018 \ \text{Pa}\]which is 29,018 pascals, and the lift coefficient the aircraft needs at that pressure is small,
\[C_L = \frac{W}{qS} = \frac{151{,}240}{29{,}018 \times 41.81} = 0.1247\]The wing’s aspect ratio is $b^2/S = 2.42$, so with an assumed Oswald efficiency of 0.75 the induced drag coefficient is
\[C_{D_i} = \frac{C_L^{2}}{\pi \, \mathrm{AR} \, e} = \frac{0.1247^{2}}{\pi \times 2.42 \times 0.75} = 0.002726\]which is negligible, so the dash is a pure zero-lift and wave-drag problem. Adding an assumed subsonic zero-lift coefficient of 0.018 and a wave-drag increment of 0.017 at the transonic peak,
\[C_D = C_{D_0} + C_{D_w} + C_{D_i} = 0.018 + 0.017 + 0.002726 = 0.03773\] \[D = q S C_D = 29{,}018 \times 41.81 \times 0.03773 = 45{,}771 \ \text{N} = 10{,}289 \ \text{lbf}\]Thrust available falls with density, and taking the usual power-law form,
\[T = T_{\text{SL}} \sigma^{n} = 40{,}000 \times 0.4481^{0.7} = 40{,}000 \times 0.5701 = 22{,}805 \ \text{lbf}\]so 22,805 pounds force is available, against a drag of 10,289.
The exponent is assumed and the conclusion does not depend on it. Across values from 0.6 to 1.0 the thrust available runs from 24,711 down to 17,925 pounds force and the ratio of thrust to drag from 2.589 to 1.878, so the margin survives the range. Taking the build-up,
\[\frac{T}{D} = \frac{22{,}805}{10{,}289} = 2.216 \qquad \text{or} \qquad \frac{D}{T} = \frac{10{,}289}{22{,}805} = 0.451\]so holding the dash uses 45.1 percent of the thrust available. The ratio of 2.216 stands against 2.389 from a lumped coefficient of 0.035, which would have given a drag of 9,546 pounds force. The two estimates differ by eight percent and neither is close to the value that would make Mach 1.05 difficult.
The aircraft was not working to hold Mach 1.05. It was flying at the target speed of the test, on a demonstrator that reached Mach 1.2 on a later flight of 26 July, and the 9 July sortie had already reached Mach 1.08.
The Vertical Landing Was the Easiest of the Three
The vertical landing came last, which means it came at the lowest weight of the sortie. Every pound of fuel burned during the climb, the dash and the recovery is a pound the lift system does not have to hold up.
With the same assumed burn of 3,500 pounds the landing weight is $W_{\text{land}} = W_{\text{TO}} - W_{\text{fuel}}$, and the ordering improves the margin by the factor
\[\frac{T_{\text{total}} / W_{\text{land}}}{T_{\text{total}} / W_{\text{TO}}} = \frac{W_{\text{TO}}}{W_{\text{TO}} - W_{\text{fuel}}}\]which needs no thrust figure at all. Across the takeoff-weight bracket of the previous section,
| Takeoff weight, lb | Takeoff margin | Landing weight, lb | Landing margin | Gain from the ordering |
|---|---|---|---|---|
| 34,197, the floor | 1.225 | 30,697 | 1.365 | 1.114 |
| 45,697, the ceiling | 0.917 | 42,197 | 0.993 | 1.083 |
The ordering helps across the bracket, but it does not rescue the ceiling. The landing is always the lightest point of the sortie and the gain from the ordering runs from 1.083 to 1.114, but at the ceiling the landing margin is 0.993, and after the 3.354 percent loss of a ten kelvin inlet rise it falls further,
\[\frac{T_{\text{total}}}{W_{\text{land}}} \cdot \frac{T_{\text{amb}}}{T_{\text{amb}} + \Delta T} = \frac{41{,}900}{42{,}197} \times \frac{288.15}{298.15} = 0.960\]The vertical landing that ended Mission X therefore bounds its takeoff weight. With the assumed burn the landing weight lies within the sea-level vertical thrust only for a takeoff weight below 45,400 pounds, which excludes the top of the bracket. At the round 40,000 pounds of the 2001 releases the bound is 43,500 pounds, and a hot day lowers it further. What the bracket removes is the single figure. The documented 34,000 pounds of 26 July lies below the floor of the bracket, and with the assumed burn it would imply a landing weight of 30,500 pounds, under the empty weight the bracket uses, so it is not a Mission X case.
The three events were flown in the order that makes each of them easiest. The short takeoff came first, when the aircraft was heaviest and a rolling start was most useful. The supersonic dash came in the middle, where it burned the fuel. The vertical landing came last, when the aircraft was lightest and the manoeuvre most comfortable. An operational sortie would be flown in that order too, so the profile is not being criticised. It does not test a worst case, and it was never claimed to.
The worst case for this architecture is a vertical landing at high weight with stores still aboard, which is the bring-back problem the previous article examined in detail for the rival. Mission X did not go near it.
What the Data Changed
The Answer
Mission X was evidence for one proposition and display for another, and the two are easy to conflate.
It is genuine evidence that the installation requires no reconfiguration between hovering and supersonic flight. That is a real architectural property, the rival did not have it, and a single sortie moving through both regimes demonstrates it as directly as anything could.
It is not evidence that the combination itself was new, and a claim often made for Mission X is wrong. The Yakovlev Yak-141 was a supersonic design that first flew in 1987 and made its first full transition in 1990, so a vertical-landing aircraft capable of supersonic flight without reconfiguration existed more than a decade earlier. What was new on 20 July 2001 was the sequence in one sortie, not the capability.
It is not evidence that any of the three regimes was individually difficult for this aircraft, because the arithmetic shows that none of them was. The short takeoff was flown by an aeroplane that could have gone straight up unless it carried nearly full internal fuel, and its fuel load is not on record. The supersonic dash, as computed under The Supersonic Leg Was Thermally Free, raised the stagnation temperature by three kelvin over a sea-level standard day and used 45.1 percent of the thrust available. The vertical landing happened at the lightest the aircraft had been on that sortie.
And the sortie was not where the engineering risk was retired. Every element had been flown already, the first in-flight conversion had happened on 9 July, and that sortie went faster. The information was retired on 9 July and the demonstration was performed on 20 July.
No one is at fault here. A demonstration exists to make something legible to people who will not read a flight test report, and Mission X did that better than any report could. But a flight that transfers no new information to the engineers and a great deal to everyone else is a display, and calling it by its name costs the programme nothing.
What the Programme Settled
The programme established that a shaft-driven lift fan works on an aeroplane, which had never been shown at this scale or this power, and the team received the Collier Trophy for 2001 on that basis. The fan’s open literature began before the flights and continued after them. The shaft-driven lift fan propulsion system and lift concept for the Joint Strike Fighter are described in Bevilaqua 1997 and Winfree 1998, and the fan is treated in a study of the flow characteristics of a shaft driven lift engine in 2002 and a forced response analysis of a shaft-driven lift fan in 2003. It established that the clutch, gearbox and drive shaft survive repeated engagement in flight. It established that mode conversion can be flown as a routine event rather than as a test point. And it established, by the counter-rotation argument above, that a fan of this power can be installed without consuming the aircraft’s roll authority.
What It Fed Into
The architecture went into production essentially unchanged in principle, which is unusual. The production lift system kept the shaft drive, the counter-rotating fan, the clutch, the three-bearing swivel module and the roll posts.
The literature followed the aircraft and left the designation behind, the mirror image of the previous two articles’ finding. The X-33 and the X-34 each all but stopped generating literature under their own names once they were cancelled, and this article’s subject shows the control case. The X-35’s own trace is also thin, and for the opposite reason. The work did not stop. It changed name.
What It Failed to Influence
The demonstration did not settle the weight question, which the production programme had to answer next. In 2004 engineers removed more than 2,700 pounds of unwanted estimated weight from the STOVL design, and nothing in the 2001 campaign predicted that need or could have. A demonstrator that weighs 34,000 pounds tells you very little about an aeroplane that will weigh far more, and the architecture’s thrust margin is the quantity that weight growth attacks.
The Contemporary Literature
| Cluster | Records |
|---|---|
| Powered lift, V/STOL and STOVL aircraft | 847 |
| Flight control, control allocation and handling qualities | 287 |
| Jet impingement, ground effect and hot gas ingestion | 318 |
| Electric, distributed and hybrid propulsion and electric vertical takeoff | 434 |
| Rotors, propellers, actuator discs and momentum theory | 400 |
| Transonic and supersonic drag | 151 |
| Fan, compressor and counter-rotating stages | 273 |
| Clutches, gears and drivetrains | 202 |
| Inlets, intakes and diffusers | 291 |
| Engines, thrust and installed performance | 153 |
| Nozzles and thrust vectoring | 197 |
| Lift fans, ducted fans and the fan in the wing | 226 |
| Fighter programmes, defence acquisition and cost | 109 |
| Weight, sizing and aircraft design | 46 |
| Aircraft performance, takeoff, landing and ship operation | 66 |
| Kinematics of joints, mechanisms and manipulators | 142 |
| The atmosphere, temperature and aerodynamic heating | 20 |
| Fuels and fuel properties | 23 |
| Aircraft, jet and rotor acoustics | 21 |
| Ejectors and thrust augmentation | 90 |
| High-temperature and rotating seals | 15 |
| Total | 4,311 |
This article surveys the current literature on its subject as well as studying its aircraft. For this subject the survey is unusually rewarding, because almost every question the X-35 raised is being asked again now by people building other kinds of vehicle.
Powered Lift Moved to Electric Aircraft and Took the Physics With It
The single largest change since 2001 is that the momentum theory in this article stopped being a military speciality. Disc loading, figure of merit, hover efficiency and outwash are now the working vocabulary of electric vertical-takeoff aircraft, and nearly all of that literature is recent. Of the 434 records in the cluster on electric, distributed and hybrid propulsion below, 415 were published in 2015 or later. Distributed and hybrid electric propulsion are reviewed in Kim et al 2018 and Wall and Meyer 2017, and the actuator disc is applied to rotor and wing interaction in hover in Chen and Hubner 2020 and to rotor flow in Barakos et al 2020. Records on the momentum theory they share form the cluster on rotors, propellers, actuator discs and momentum theory.
The relation is identical and the answer comes out the other way. Thrust per unit power is inversely proportional to jet velocity, so a designer free to choose disc area will choose a large one. The X-35’s fan sits at 70.2 kilopascals of disc loading because it had to fit inside a supersonic fighter. An electric aircraft with no such constraint runs a far lower disc loading and gains enormous hover efficiency from it. The X-35 is the extreme high-disc-loading end of the trade the current literature explores at the other end.
The Lift Fan Itself
The shaft-driven lift fan remains a nearly unique artefact and its literature is correspondingly small. Of the research records in this survey, 70 name a lift fan in their titles, and 43 of those date from 1975 or earlier. What has grown instead is the turbomachinery beneath it. Counter-rotating stages, which the X-35 adopted for the torque reason set out earlier, are now studied for their own aerodynamic merits, and 76 of the 105 titles that name counter-rotation or contra-rotation date from 2015 or later. The modern work on two-stage counter-rotating design and on matching the speeds of the two rotors, in Sun et al 2017 and Ai et al 2018, and the ducted contra-rotating lift fan of Deng and Ren 2017 are where a reader should go for the fan itself rather than to anything carrying the aircraft’s name. The clusters on lift fans, ducted fans and the fan in the wing, and on fan, compressor and counter-rotating stages, hold these records.
The Force the Conversion Makes Has Moved to Electric Aircraft Too
The momentum drag this article computes has almost no contemporary literature under that name and a large one under others. One research record names momentum drag or ram drag in its title, the transition strategy for an annular lift fan aircraft of Jiang and Zhang 2021. A vehicle that ingests air through a lifting device while moving forward meets the identical problem, and the vehicles doing that now are electric.
The modern vocabulary is boundary layer ingestion, distributed propulsion installation and the tiltrotor or tiltwing conversion corridor. The last of those is the closest analogue, because this article examined a conversion corridor when it found that the X-35B engaged its fan at 180 knots while flying conventionally, with the wing already carrying the whole weight. The corridor is optimized in Righetti et al 2017, its interaction effects are treated in Appleton et al 2021 and Tran and Lim 2022, and it is derived for an electric tiltrotor in Choi et al 2025. The corridor records fall under the cluster on powered lift, V/STOL and STOVL aircraft, and the boundary layer ingestion records under the cluster on inlets, intakes and diffusers. An electric vehicle with many rotors faces the same trade between converting early, where the lift system must carry weight, and converting late, where it must absorb drag.
The Swivel Module’s Kinematics Live in Robotics Now
The canted-joint geometry in this article has a small aeronautical literature and a large one elsewhere. Since 2014 a few papers treat the three-bearing swivel duct nozzle itself, its deflection control in Wei et al 2019, a scaled nozzle and its rotary drive in Xiangyang et al 2019 and Qi et al 2020, and a design method in Shi et al 2026. Spatial mechanisms, constant-velocity couplings and the synthesis of linkages that convert rotation into controlled angular deflection are studied far more widely in robotics and machine design, as in Kong 2016 and Arrouk et al 2018, and the kinematics are best read there. The cluster on kinematics of joints, mechanisms and manipulators collects them.
The high-temperature rotating seal is the part that stayed aeronautical, because it is the requirement that makes the mechanism hard rather than the geometry. The thermal protection of the swivel nozzle’s bearings is the subject of Zhang et al 2025 and Jinxin et al 2026, and the cluster on high-temperature and rotating seals lists that work.
Fuel Density Became an Active Subject
The fan-bay calculation in this article assumes a fuel density, and in 2001 that would have been a table lookup. It is now a research subject, because sustainable aviation fuels and their blends have densities that differ from conventional kerosene, and a volume-limited aircraft feels that difference directly. The density of jet fuel blends is predicted in Kurt 2026, high energy density fuels are designed in Rijal et al 2025, and the volume swell of drop-in fuels is modelled in Kosir et al 2020. The rest of the cluster on fuels and fuel properties concerns the composition and properties of alternative fuels and their effect on engine performance and on aircraft missions. An aeroplane that gave up three thousand pounds of fuel volume to carry a fan is the kind that would.
The Ground Environment Became a Computational Subject
Hot gas ingestion was being computed by 1990, and its literature stops with the programme. The hot gas environment around a STOVL aircraft in ground proximity is measured in Sullivan and Murthy 1990 and computed in Tafti and Vanka 1990, ingestion is calculated in VanOverbeke and Holdeman 1990, and the environment of a hovering jet STOVL aircraft is set out in Kuhn et al 1993. Every one of the 28 research records whose titles name hot gas ingestion, recirculation or environment, or reingestion, was published between 1968 and 2002.
What became computational is jet impingement, and the shift is one of proportion. Of the 205 records in the cluster on jet impingement, ground effect and hot gas ingestion published through 2001, 26 name a computational method in their titles, against 36 of the 88 published from 2015 onward. The unsteady pressure and thermal loading a landing surface sees is measured and computed in Hromisin et al 2015 and Crowell and Myers 2016, and supersonic impingement on a jet blast deflector and on a carrier deck is treated in Worden et al 2016 and Yue et al 2015.
Drivetrains, Clutches and the Energy That Has to Go Somewhere
The halving identity in this article is drivetrain knowledge, and the literature that holds it is largely automotive and rotorcraft. Of the 121 research records whose titles name a clutch, six name an aviation, aerospace or STOVL use, among them Bian et al 2025 and the dry friction clutch of STOVL aircraft in Zhu et al 2026, and the engagement of a shaft-driven lift fan is modelled and controlled in Jiang et al 2023. The contemporary work on dry and wet clutch thermal modelling, as in Pisaturo et al 2015 and Xiaozeng et al 2015, applies directly to the scheduling of a mode change, and rotorcraft drive systems appear in Stevens et al 2015. All of these sit in the cluster on clutches, gears and drivetrains.
Transition, Control Allocation and Hovering
Control allocation is almost entirely a recent literature. An aircraft with more effectors than axes has to decide how to distribute a demand among them, and in 2001 that was a specialist topic within powered lift. It is now a general problem in flight control, driven by electric aircraft with many rotors and by tailless configurations. Of the 105 research records whose titles name control, thrust or torque allocation, 96 were published in 2015 or later. Allocation is applied to a tailless aircraft with innovative control effectors in Matamoros and de Visser 2018, to a hexacopter in Nguyen et al 2018 and to a tilt-rotor in its transition in Zhang et al 2019, and the general problem is surveyed for marine vessels in Johansen 2016. The cluster on flight control, control allocation and handling qualities holds this work.
Nozzles, Inlets and Installed Performance
Thrust vectoring outlived this application, and much of its recent literature turns the jet without moving the nozzle. Of the 101 research records from 2015 onward whose titles name thrust vectoring or vectored thrust, 42 concern fluidic methods, by secondary injection, bypass ducts, dual throats, shock vectoring, counterflow, coflow or the Coanda effect, as in Das et al 2024, Kara and Kurtuluş 2024 and Shukla et al 2026. The diverterless inlet passed from the demonstrator to the production aircraft, whose redesigned three-sided cowl retains the diverterless design, and boundary-layer ingestion into a diverterless intake is measured in Rein and Koch 2015. Installed performance accounting, the proper home of the thrust lapse in this article’s dash calculation, remains the least glamorous and most consequential part of the subject, as installed performance seeking control in Sun et al 2015 shows. Three clusters cover this ground, those on nozzles and thrust vectoring, on inlets, intakes and diffusers, and on engines, thrust and installed performance.
Performance, Weight and the Programme
Weight growth is the subject this article’s aircraft failed to illuminate, and the literature in this survey treats weight as something to estimate rather than to track. No research title in the survey names weight growth. The 26 titles that name weight or mass estimation treat it as a design method, as in Nigam et al 2015, Dababneh and Kipouros 2018 and Horvath and Wells 2018. The production programme met the other side of the question after the demonstrator had answered every question it was asked, when more than 2,700 pounds of unwanted estimated weight had to be removed from the STOVL design in 2004, and in this survey weight as a programme risk appears only indirectly, through cost growth, as in Gideon and Wasek 2015. They appear in the clusters on weight, sizing and aircraft design, and on fighter programmes, defence acquisition and cost.
Acoustics Became a Binding Constraint Somewhere Else
Noise barely constrained the X-35 and it constrains its successors severely. The acoustic literature around vertical lift has grown because community acceptance is now a design driver for civil vertical flight in a way it never was for a fighter demonstrator at Edwards. The community noise of vertical takeoff personal air vehicles is predicted in Kim et al 2016, and the acoustic environment of the production aircraft’s own vertical landings and of short takeoffs from a carrier is measured in Reichman et al 2016 and Wall et al 2017. The cluster on aircraft, jet and rotor acoustics contains them.
Method, Uncertainty and Computation
The methodological change since 2001 is larger than any single technical one. Uncertainty quantification, surrogate modelling and machine learning now sit between the wind tunnel and the design, and a reconstruction of the kind this article performs by hand would today be posed as an inference problem with stated priors, as the probabilistic flight envelope of an over-actuated aircraft in Yin et al 2019, the neural-network system identification of Harris et al 2016 and the kriging-assisted ducted fan optimization of Qing et al 2019 illustrate. That is better practice and it would not have changed any conclusion here, because the quantities that mattered were bracketed rather than estimated. These records sit in the clusters on flight control, control allocation and handling qualities, and on lift fans, ducted fans and the fan in the wing.
Powered lift, V/STOL and STOVL aircraft
Powered-lift aircraft of every kind, from the period jet-lift and lift-fan concepts and the Harrier to tiltrotors, tailsitters and the hover and transition of unmanned vertical-takeoff vehicles. Of these records, 545 were published in 2001 or earlier, and 234 in 2015 or later.
847 records. [A Novel Sliding Mode Controller for Underactuated Vertical Takeoff and Landing Aircraft 2020] [Adamson 1968] [Adelt 1983] [Adibhatla 1993] [Adibhatla 1994] [Advanced Short Takeoff and 1995] [Ahmed Snikdha and Chen 2023] [Ahn et al 2023] [Alexander et al 1986] [Alscher et al 1966] [An H infinity loop-shaping design 2000] [Anderson 1983] [Anderson and Foster 1984] [Anderson et al 1983] [Anderson 1979] [Anderson and Schroers 1972] [Anderson 1960] [Andrew 1972] [Appleton et al 2021] [APPLICATION OF FLUIDIC THRUST VECTORING IN V/STOL AIRCRAFT 2024] [Armutcuoglu et al 2004] [Aroussi 2026] [Asri et al 2019] [Assessing Competitive Strategies for 2001] [Atkinson et al 2013] [Aulehla and Kissel 1982] [Autelitano et al 2016] [Axelson and Upton 1970] [Axten and Johnson 2020] [Axten and Johnson 2021] [Bach and McNally 1988] [Balaban and Erdem 2022] [Banazadeh and Taymourtash 2016] [Bando et al 1993] [Baron 1983] [Bates et al 2003] [Bath et al 2021] [Bath et al 2022] [Bath et al 2023] [Batterton and Blaha 1987] [Beans 1995] [Bear et al 1979] [Beard and Foley 1983] [Beard and Foley 1982] [Bedford 1962] [Beilman 1983] [Beisbier 2002] [Bell Aerospace Co Buffalo Ny 1970] [Belluomini et al 2023] [Berg et al 1988] [Bertelsen 2016] [Berton et al 2000] [Bevilaqua 2009] [Bevilaqua 2009] [Bhagwat 2013] [Bhandari and Chakraborty 2026] [Bhardwaj and Holzapfel 2024] [Biesiadny et al 1993] [Biesiadny 1991] [Birckelbaw and Nelson 1992] [Birckelbaw 1992] [Birckelbaw et al 1994] [Birkler 2001] [Bishop et al 2000] [Blaha and Batterton 1990] [Bland 1971] [Bodden and Virnig 1994] [Bode et al 1978] [Bogdan 2015] [Boles and Stockman 1979] [Borchers et al 1992] [Boruff and Roch 1981] [Bottorff 2004] [Bowling et al 1969] [Brady and Gururajan 2025] [Brady and Gururajan 2026] [Breul 1963] [Brown 1965] [Brown 1989] [Brown and Fischer 1967] [Brown and Fisher 1968] [Brown et al 2009] [Brown 1978] [Buchholz 2002] [Bucknell 1987] [Bucknell et al 1990] [Bulat and Minin 2017] [Bulat and Minin 2018] [Butler et al 1966] [Caffee 1985] [Caldwell and Lafavor 1980] [Calise and Kramer 1982] [Calvano and Harney 1998] [Calvert 1997] [Camacho 1991] [Campbell and Quinn 1974] [Campos 2001] [Cao et al 2022] [Cappetta 1993] [Cardenas 2022] [Carico and Garcia-Otero 1995] [Carlson and Zhao 2002] [Carpenter and Gotlieb 1970] [Carpio-Alemán et al 2016] [Carr 1984] [Cassinelli et al 2023] [Chaderjian et al 2002] [Chaitanya et al 2025] [Challier and Hey worth 1964] [Chance Vought Corp Dallas Tx 1979] [Chang et al 2018] [Chapman 2018] [Chapman 2018] [Chapman 2018] [Chapman 2018] [Chapman 2018] [Chapman 2018] [Chapman 2019] [Chen et al 2004] [Chen et al 2018] [Chen et al 2019] [Chiappinelli et al 2019] [Chin 1988] [Chou and Hwang 1984] [Chow 1993] [Blanken and Whalley 1993] [Chung et al 1993] [Chung et al 1993] [Clark 1965] [Clark and Vasta 1984] [Clark et al 1982] [Clark 1975] [Clark 1980] [Clough 1990] [Clymer and Flora 1973] [Cochrane and Boissevain 1978] [Coe and Riley 1988] [Cohan and Hirsh 1966] [Coles 1968] [Conference on V/Stol Aircraft 1960] [Conlon and Bowles 1977] [Conlon and Bowles 1978] [Conner and Wellman 1994] [Coolican 2002] [Coons 1987] [Coopmans et al 2022] [Coplin 1966] [Corle et al 2019] [Corliss et al 1977] [Corliss et al 1978] [Coty and Kesling 1967] [Cox and Abbott 1966] [Cox and Kirby 1986] [Cox and Roskam 1990] [Crafa and Reed 1980] [Crandall et al 1973] [Crossley and Rutherford 1995] [Cui et al 2019] [Cummings and Hall 2002] [Cunningham and Boytos 1988] [Curry et al 1965] [Curtiss 1970] [Curtiss 1971] [Curtiss and Howard C. 1969] [Daud Filho and Belo 2023] [Davenport et al 1972] [Decker 1966] [de Matteis et al 1998] [De Persis et al 2001] [Decoupling Inversion Tracking Control of Underactuated Vertical Takeoff and Landing Aircraft 2024] [Defense Science Board Washington Dc 1979] [DeHoff 1979] [DeJesus 2013] [Del Bianco et al 1997] [Denham 2002] [Denham and Paines 2008] [Denning and Mitchell 1986] [Design and Aerodynamic Analysis of a VTOL Tilt-Wing UAV 2021] [Design of the circulation control wing STOL demonstrator aircraft 1979] [Desilets] [Deveaux 1965] [Di et al 2025] [Diekmann 2017] [Digital Engine Control for V/STOL and V/TOL Aircraft 1982] [Dinca et al 2019] [Doff-Sotta et al 2025] [Dolan 1964] [Dollyhigh et al 1984] [Dong et al 2021] [Dorr et al 1992] [Douglas et al 1990] [Drinkwater and Rolls 1962] [Drinkwater et al 1965] [Dukes 1970] [Durston and Smith 1981] [Durston and Stonum 1987] [Durston and Stonum 1988] [Dyke 1963] [Egerton and Fitzpatrick 1967] [Eilertson 1977] [Elliott and Schreiber 1964] [Elliott and Simmons 1987] [Enenakpogbe et al 2025] [Engelland 1991] [Englar 1974] [Englar 1975] [Englar 1987] [Englar 1988] [Englar and Campbell 2002] [Englar and Campbell 2002] [Englar and Kirkpatrick 1969] [Englar et al 1977] [Eshleman et al 1986] [Esker and Debonis 1991] [Fan et al 2022] [Fan et al 2025] [Farley 1968] [Farley 1971] [Farris et al 1983] [Faye 1960] [Feddersen and Cea 1977] [Fejtek and Roberts 1992] [Felker et al 1986] [Feng Lin et al 1999] [Fenwick 1967] [Ferrier et al 2024] [Fielding 1982] [Fielding and Lodge 2000] [Final Assembly and Checkout 2002] [Fletcher 1962] [Flow visualization studies of the internal flow characteristics in asimulated mixed flow vectored thrust ASTOVL engine configuration 1991] [Foley and Woodrey 1980] [Foster et al 1987] [Fozard 1978] [Fozard 1979] [Fozard 1986] [Franciscus and Luidens 1984] [Franklin 1993] [Franklin 1993] [Franklin 1994] [Franklin 1996] [Franklin and Engelland 1991] [Franklin and Engelland 1993] [Franklin and Innis 1977] [Franklin and Stortz 1993] [Franklin et al 1986] [Franklin et al 1988] [Franklin 1986] [Franklin and Anderson 1984] [Franklin and Innis 1972] [Franklin and Innis 1974] [Franklin and Innis 1980] [Franklin 2000] [Franklin and Stortz 1989] [Franklin et al 1989] [Franklin et al 1990] [Fredericks et al 2015] [Fredericks et al 2016] [Frey 2011] [Friend 1964] [Frost and Bishop 1963] [Frost et al 2002] [Furey 1983] [Gainutdinova and Gainutdinov 2018] [Galdieri et al 1992] [Gallops et al 1990] [Gamon 1988] [Garg 1993] [Garg and Mattern 1991] [Garg and Mattern 1994] [Garg and Ouzts 1991] [Garg and Schmidt 1993] [Garg et al 1990] [Garner 1967] [Gaston et al 1984] [Gea et al 1991] [George 1999] [Gerken 1979] [Gero 2001] [Getachew and Zeleke 2024] [Gibs et al 1975] [Gielow 1971] [Gilbert 1985] [Gingras 1999] [Giurca 2014] [Goland et al 1964] [Goldberger 1966] [Gorham 1977] [Govdeli et al 2019] [Green and Andrews 1989] [Green and Bogle 1991] [Green and Zeckhauser 2019] [Greene 1977] [Greif et al 1972] [Griffin 1983] [Groen 1988] [Grunwald 1964] [Guan et al 2025] [Hahn and Wilson 1985] [Hahn and Wilson 1985] [Hall 1965] [Hange et al 1996] [Hange et al 1996] [Harding] [Hariharan et al 2017] [Haro 2003] [Harradine 1977] [Hart et al 2025] [Hartmann et al 2016] [Hartmann et al 2017] [Hartnett and Mittlesteadt 2000] [Hatta and Matsuki 1964] [Havey and Kline 1989] [Hebbar et al 1999] [Hebert et al 1970] [Hebert et al 1973] [Hegarty et al 1965] [Hegde 2020] [Hegde et al 2019] [Helicopter and V/Stol Aircraft] [Henderson 1964] [Henderson and Walters 1981] [Hess 1977] [Hess 1988] [Hill 1966] [Hill 1970] [Hill 1981] [Hill and Jenkins 1979] [Hindson et al 1982] [Hirsh 1965] [Ho et al 2019] [Hoffman 1971] [Hoh and Mitchell 1983] [Hollingsworth et al 1977] [Holzhauser et al 1972] [Hong et al 2025] [Hong et al 2025] [Hooker 1981] [Hoskin 1993] [Hoskin et al 1991] [Hsin 1974] [Hu et al 2024] [Hu et al 2024] [Hua et al 2025] [Huan et al 2021] [Huang et al 2020] [Huang et al 2022] [Huang et al 2022] [Huang et al 2024] [Hughes 2017] [Huntley 1972] [Hutchison et al 1983] [Hyde and Glover 1991] [Hynes et al 1989] [Ilyas et al 2023] [Imhof and Schork 1999] [Integration and simulated flight 1977] [Invernizzi et al 2018] [Irvin and Swan 1956] [Isidori et al 2001] [Franklin 1993] [Jang et al 2022] [Jenista and Sheridan 1987] [Jeong et al 2026] [Jewell et al 1979] [jian-jian et al 2019] [Jiang et al 2023] [Jimenez-Garcia et al 2017] [Jin and Zhao 2025] [Jo and Kwon 2019] [Johns 1998] [Johnson and Craig 1974] [Johnson 2003] [Johnston 1965] [Johnston and Friend 1965] [Johnston et al 1965] [Jones 1966] [Jones 2014] [Joppa 1969] [Kai 2024] [Kakavitsas et al 2024] [Kalemaris and Cea 1977] [Kandath et al 2019] [Kandel et al 2022] [Kang 2022] [Kanistras et al 2016] [Kappus 1969] [Kapstein 2004] [Kazan and Krause 1968] [Kazan and Krause 1967] [Keller 1969] [Keller et al 2018] [Kentfield 1967] [Key 1971] [Kidwell 1981] [Kidwell and Rapp 1985] [Kidwell and Lampkin 1983] [Kim and Jo 2025] [Kim et al 2016] [Kim et al 2025] [Kimberlin 1987] [Kinzer 2008] [Kleckner 1973] [Klinar and Craig 1961] [Klingloff et al 1965] [Knott 1977] [Koenig et al 1977] [Kohn 1972] [Kohn 1983] [Koncsek and Syberg 1977] [Kozapalli and Warmbrodt 1997] [Krammer and Holzapfel 2023] [Krenkel and Salzman 1968] [Krepski and Hudson 1981] [Krimphove et al 2023] [Krosche and Heinze 2015] [Kuang and Zhu 2015] [Kuhn 1979] [Kuhn 1980] [Kuhn 1981] [Kulhánek et al 2023] [Kumon et al 2010] [Kuntz et al 1997] [Kurylowich and Ritter 1970] [Lacey and Miller 1977] [Lacey et al 1979] [Landy and Kim 1984] [Laudeman 1972] [Lavi 1966] [Lavi 1967] [Lebacqz and Radford 1978] [Lebacqz and Radford 1979] [Lee et al 1988] [Leovan 2019] [Levin et al 2018] [Levine and Inglis 1989] [Levinsky and Ramsey 1972] [Levinsky et al 1968] [Levinsky et al 1969] [Levinsky et al 1970] [Lewis 1989] [Lewis 2000] [Lewis and Lewis 1981] [Lewis and Simpkin 1981] [Li and Xia 2018] [Li et al 2018] [Li et al 2023] [Li et al 2024] [Liao and Bang 2023] [Liao et al 2024] [Lichota 2023] [Lift Loss In Hover 2007] [Lim and Jung 2025] [Lind and Tamplin 1981] [Linnell 1963] [Lipera and Sandlin 1984] [Liu and Zhang 2024] [Liu et al 2019] [Liu et al 2022] [Liu et al 2022] [Liu et al 2022] [Liu et al 2024] [Liu et al 2025] [Liu et al 2026] [Lollar and Matous 1963] [Lollar et al 1965] [Lopez and Shen 1971] [Loth and McCormick 1986] [Loth et al 1974] [Loth et al 1976] [Lou et al 2024] [Louthan 1980] [Love 1993] [Lowenberg and Jones 2003] [Lozano et al 2022] [Lu and Terrier 2003] [Lu and Terrier 2003] [Lu et al 2017] [Lu et al 2019] [Lu et al 2022] [Pyle 1971] [Saari 1958] [Maddock et al 2011] [Maisel and Harris 1981] [Maita et al 1983] [Maita et al 1990] [Makarov 2019] [Mange et al 2002] [Manley and von Klein 2002] [Manoilo 2025] [Mansell 1987] [Marchese 1963] [Marconi et al 2002] [Margason 2002] [Margason and Hoad 1979] [Margason and Kuhn 1988] [McKinney and Kirby 1964] [Mathews 1987] [Mathews and Rothstein 1998] [May and Widdison 1971] [May et al 2024] [May et al 2024] [May et al 2026] [McCarthy 1992] [McCarthy 2002] [McCarthy and Kelly 1993] [McConnell 2006] [McCormick 1969] [McIntyre 1963] [McNally 1986] [McNally and Bach 1988] [Meiklem 1969] [Melo et al 2026] [Mendenhall and Spangler 1976] [Mendenhall et al 1972] [Merewether 1963] [Merrick 1981] [Merrick et al 1991] [Merrick 1982] [Merrick 1984] [Meyer et al 1991] [Michaels 1969] [Michaelsen 1971] [Migbee et al 1987] [Mihalik and Keane 2022] [Mihaloew and Weiss 1989] [Mihaloew et al 1981] [Mihaloew and Drummond 1989] [Miller 1973] [Miller et al 1981] [Mitchell et al 1992] [Mixson et al 1975] [Miyazaki and Tsubakino 2017] [Mo et al 2024] [Moller 1985] [Moller 1998] [Momiyama 1977] [Moorhouse 1990] [Moralez et al 1987] [Moss 1995] [Moustafa et al 2025] [Mrusek 2021] [Mueller et al 2016] [Murakoshi 1969] [Murata et al 2025] [Murata et al 2025] [Mysko et al 1993] [Nakaguchi 1967] [Naldi and Marconi 2009] [Naldi and Marconi 2011] [Naldi and Marconi 2013] [Nalls and Stortz 1993] [NASA Conference on V/STOL 1960] [Naumowicz et al 1998] [Naumowicz et al 1996] [Nelms 1978] [Nelms 1984] [Nichols and Englar 1980] [Nishimura 1980] [Nithya and Rashmi 2019] [Norman et al 2018] [O’Brien and Delgado 2024] [O’Rourke and Rutherford 1991] [Okumoto and Elsanker 1973] [Okuno and Kawachi 1993] [Okuno and Kawachi 1993] [Omar and Lampkin 1977] [Operational Aspects of the 1969] [Ornelas 1985] [Ostheimer and Giguere 1963] [Owens et al 2004] [Pang et al 2024] [Patierno and Asdurian 1965] [Pauli et al 1970] [Paulson 1981] [Paulson 1980] [Pavlov 2016] [Payne and Henry E. 1961] [Payne and McConnell 2004] [Pei et al 2023] [Peloquin et al 2017] [Peng et al 2015] [Petit and Scholey 1973] [Petrov 1993] [Petrov 1993] [Philhower et al 1998] [Pieper 1965] [Pirera 1983] [Pisano et al 2025] [Platt 1991] [Platzer and Margason 1976] [Polak and George 1998] [Postlethwaite 1998] [Postlethwaite and Bates 1999] [Powered-Lift Aerodynamics and Acoustics 1976] [Price 1964] [Price 1964] [Pruyn and Taylor 1971] [Pryce and Hirschberg 2003] [Pryce et al 2005] [Pulk and Stolarik 1977] [Qin 2023] [Qing et al 2023] [Qiu et al 2023] [Quinto et al 1993] [Rabin 1983] [Rae Jr. 1972] [Ramesh and Subbarao 2016] [Rand 1999] [Ransone 2002] [Rapp 1985] [Rau and Babiceanu 2018] [Reichman et al 2016] [Ren and Zha 2024] [Representative Operations of V/STOL 2002] [Requirements for STOVL integrated flight/propulsion control system 1994] [Rhoades and Ybarra 1980] [Kuhn and McKinney 1965] [Richardson 1966] [Riddle et al 1981] [Riesenfeld 1968] [Righetti et al 2017] [Riley et al 1989] [Ringland 1977] [Roberts 2002] [Robinson 2015] [Rolls and Aoyagi 1977] [Roltgen and Byrnes 1991] [Romine et al 1989] [Roth 1993] [Roth 1997] [Roth 1993] [Ruan et al 2025] [Rudolph 1972] [Ryan 1986] [Saddington and Knowles 1999] [Saddington and Knowles 2001] [Saetti 2025] [Sagan et al 2021] [Saghafi and Banazadeh 2006] [Saghafi and Banazadeh 2007] [Salahudden et al 2024] [Salisbury 2026] [Sambell 1972] [Sanchez-Rivera et al 2020] [Sanders 1964] [Sandlin and Howard 1991] [Sandoz et al 2018] [Saripalli 1995] [Saripalli and Farrell 1993] [Schaefer and Velten 1971] [Schaeffler et al 1967] [Schierman and Lowell 1992] [Schmitz 1969] [Schneider 1989] [Schneider and Watt 1988] [Schroeder and Merrick 1990] [Schwartz and Shearer 1964] [Scientific and Technical Information Division 1966] [Scopes 2001] [Seitz and Goodson 1973] [Sellers and Szuch 1973] [Semelka and Rauleder 2026] [Senkans et al 2021] [Serkin 2025] [Serovy and Kavanagh 1974] [Shanks et al 1993] [Shanks et al 2018] [Sheng et al 2022] [Sheridan 1986] [Sheridan 1983] [Sherman 1964] [Sherman and Usab 1974] [Shin and Lee 2023] [Shovlin 1978] [Showers 1980] [Silva] [Silva et al 2017] [Silva et al 2019] [Silva-Martinez et al 2015] [Sinacori 1970] [Sinacori 1970] [Sivrioğlu 2023] [Skelton 1968] [Smith 1966] [Smith 1996] [Smith 1996] [Smith 1997] [Smith 1997] [Smith and Berry 2000] [Smith and McArdle 1990] [Smith and McArdle 1992] [Smith et al 1973] [Smith et al 1999] [Smith 1961] [Soderman 1990] [Soderman and Foster 1988] [Solies 1992] [Sonkar et al 2021] [Spratt 1990] [Sridhar and Smith 2026] [Sridhar et al 2025] [Stapleford 1980] [Stark 2003] [Staruk and Datta 2019] [Staruk et al 2017] [Stauffer et al 1990] [Steele and Aurora 1978] [Steils 1965] [Stenberg 1983] [Stepniewski 1959] [Sternfeld and Hinterkeuser 1970] [Stewart and Paulson 1984] [STOL, VTOL, and V/STOL 1971] [Stone 2013] [Stone and Gutierrez 1972] [Strand et al 1967] [Strand et al 1967] [Structural Design of the 1969] [Struth 1999] [Stutz and Price 1964] [Sulkoske et al 1977] [Swaim 1970] [Syamsuar 2017] [Szlenkier 1972] [Sørensen et al 1996] [Tan et al 2019] [Tanakitkorn et al 2017] [Tanakitkorn et al 2017] [Tang et al 2025] [Tape and McIntyre 1990] [Terrier and Lu 2003] [The Hawker P1127 vectored thrust fighter program - Lessons learned 1990] [Tich 1991] [Tindell and Flynn 1978] [Tran and Lim 2022] [Tran and Yeo 2023] [Tran et al 2023] [Transition aerodynamics for close-coupled wing-canard configuration<149>V/STOL operations 1979] [Tullu and Jung 2026] [Turney and Allen 1980] [Urakubo et al 2023] [V/STOL propulsion control analysis 1981] [V/STOL World wide view 1971] [VAAC Harrier trials 2001] [Vagianos and Rooney 1964] [Van Dalsem et al 1990] [Van Nieuwstadt and Murray 1998] [Van Riper and Wood 2003] [Vandalsem et al 1989] [Vectored thrust 1992] [Verghese 2023] [Vertical Takeoff and Landing 2014] [Vertical/short takeoff and landing] [Viets 1974] [Vincent and Anex 1990] [Vinje and Miller 1973] [von Hlatky and Rice 2018] [VSTOL Systems Research Aircraft 1994] [Vucetic 2010] [Vucetic 2013] [Vucetic and Nossal 2013] [Nelms and Anderson 1984] [Wada et al 2022] [Waesche and Midgal 1975] [Wakefield et al 2019] [Walker and Allen 2002] [Wall 1989] [Walz 1976] [Wang and Ma 2021] [Wang et al 2018] [Wang et al 2019] [Wang et al 2020] [Wang et al 2022] [Wang et al 2022] [Wang et al 2022] [Wang et al 2024] [Wang et al 2025] [Warakomski 1979] [Ward and Lewis 1987] [Wardwell et al 1986] [Warner et al 1986] [Warren and Floden 2001] [Watson 1980] [Watson 1981] [Watson et al 1986] [Watson et al 2019] [Watts et al 1993] [Weber 1982] [Wechtler et al 2025] [Wei 2016] [Wei Yuan and Katupitiya 2013] [West 1969] [Whatley et al 1990] [White et al 1985] [Widmayer and Tomassoni 1971] [Wilken 1991] [Hindson et al 1993] [Willis 1980] [Willis 1980] [Willis and Genever-Watling 1977] [Wilson and Liperra 1984] [Wilson and White 1993] [Wilson and Wurts 1985] [Wilson et al 1997] [Wilson et al 1985] [Wilson et al 1981] [Wilson and Mahoney 1988] [Winborn 1970] [Winick 1968] [Wlezien and Ferraro 1990] [Wlezien and Ferraro 1992] [Wood 1968] [Wu et al 2019] [Xiang et al 2025] [Xu et al 2025] [Xu et al 2027] [Yackle 1992] [Yamato et al 1988] [Yamato et al 1991] [Yang et al 2024] [Yang et al 2024] [Yangping and Honggang 2018] [YAV-8B reaction control system bleed and control power usage in hover and transition 1993] [Yeo and Saberi 2020] [Yu et al 2025] [Zabinsky and Burnham 1977] [Zaffran and Erwes 2015] [Zafi and Chakraborty 2023] [Zalay et al 1980] [Zaludin and Gires 2019] [Zaludin et al 2021] [Zha and Ren 2023] [Zha et al 2024] [Zhang and Qi 2024] [Zhang et al 2019] [Zhang et al 2019] [Zhang et al 2024] [Zhao et al 2018] [Zhao et al 2024] [Zhao et al 2026] [Zhong et al 2019] [Zhou et al 2020] [Zhou et al 2022] [Zhu et al 2025] [Zikyamov and Panayotov 2025] [Zola et al 1984]
Flight control, control allocation and handling qualities
Flight control of powered-lift, hovering and over-actuated vehicles, control allocation among redundant effectors, integrated flight and propulsion control, and the handling qualities of hover and transition. Of these records, 112 were published in 2001 or earlier, and 153 in 2015 or later.
287 records. [Ahmed et al 2025] [Air Force Test Pilot School Edwards Afb Ca 1969] [Altamirano et al 2023] [Alwi et al 2015] [Amato et al 2022] [Antonakis and Biannic 2024] [Aouf et al 2002] [Ashkenas 1965] [Babinsky 2014] [Baggi et al 2020] [Baggi et al 2022] [Baldini et al 2020] [Bangert et al 1983] [Bardera and Matías-García 2022] [Bardera-Mora et al 2016] [Bates et al 2000] [Bayati and Williston 1977] [Beale and Miller 1975] [Beaufrere 1988] [Behbahani et al 2016] [Berry and Schweikhard 1976] [Bielat 1959] [Binwen Lu et al 2016] [Blaha et al 2023] [Bodson 2000] [Boland et al 1993] [Bright and Simon 1992] [Buffington 1999] [Buffington 1999] [Buffington and Buffington 1997] [Burcham et al 1990] [Burcham et al 1990] [Burcham and Batterton 1976] [Burr 1968] [Caliskan and Hajiyev 2003] [Cao et al 2022] [Carlin and Blair 1983] [Carlin and Hastings 1978] [Cassaro et al 2018] [Caton and Franke 1991] [Chen 2017] [Chen and Voulgaris 1998] [Chen et al 2026] [Chen et al 2026] [Chi et al 2022] [Collins Jr 2005] [Control authority assessment in aircraft conceptual design 1993] [Control system design using frequency domain models and parameter optimization with application to supersonic inlet controls 1976] [Craig 1965] [Csank and Connolly 2015] [Cui et al 2021] [Das et al 2024] [de Castro and Brembeck 2019] [de Castro and Brembeck 2021] [de Vries and Van Kampen 2019] [Deere et al 2003] [Deng and Tao 2025] [Ding et al 2016] [Doman and Oppenheimer 2002] [Dong et al 2020] [Dong et al 2025] [Du et al 2023] [Duan and Okwudire 2018] [Dunbar et al 2002] [Eilertson 1975] [Englar and Huson 1984] [Enns 2003] [Fan et al 2018] [Fan et al 2026] [Fan et al 2026] [Fengyu Jin et al 2018] [Fennell and Black 1982] [Flanders 1970] [Franklin and Innis 1978] [Franklin 1997] [Frazzini 1970] [Friddell and Franke 1990] [Frost et al 2009] [Fu et al 2015] [Gal-Or et al 1993] [Gao et al 2026] [Garg 1993] [Garg et al 1989] [Garg et al 1991] [Gatley et al 2000] [Gatley et al 2001] [Gatley et al 2002] [Gerdes and Hynes 1971] [Gern et al 2014] [Gilyard et al 1991] [Gilyard and Orme 1992] [Goyal et al 2025] [Griswold 2000] [Gundy-Burlet and Kaneshige 2001] [Halyo 1996] [Harefors and Bates 2003] [Harkegard 2003] [Harris et al 2016] [Henderson and Lavretsky 1999] [Hill 1987] [Hirano et al 2019] [Horn et al 2014] [Hu et al 2019] [Integrated flight/propulsion control - Methodology, design, and evaluation 1985] [Ivler and Geyer 2024] [Jackson 1970] [Jacuzzi and Granlund 2019] [Jafari et al 2022] [Jaw and Garg 2005] [Jente 2022] [Jeong et al 2019] [Jiang and Behbahani 2020] [Johansen 2016] [John et al 2018] [Kabaliswaran and Das 2026] [Kefayat and Kamali 2024] [Kostenko and Tolstonogov 2021] [Kranenburg et al 1986] [Lambregts 1983] [Lampl and Hornung 2018] [Lan et al 2025] [Larson and Schweikhard 1974] [Lehtinen and Zeller 1972] [Lei and Zha 2022] [Leitner 1986] [Li et al 2016] [Li et al 2019] [Li et al 2021] [Li et al 2022] [Li et al 2022] [Li et al 2025] [Li et al 2025] [Liang and Fu 1991] [Liang et al 2023] [Licata and Burcham 1983] [Lin et al 2019] [Lin et al 2019] [Liu and Wu 2023] [Liu et al 2015] [Liu et al 2018] [Liu et al 2018] [Liu et al 2020] [Liu et al 2021] [Liu et al 2021] [Liu et al 2023] [Liu et al 2024] [Liuqing Yang et al 2016] [Lu et al 2019] [Madeiras et al 2026] [Marques Goncalves et al 2024] [Matamoros and de Visser 2018] [Matous et al 2021] [Mattern and Garg 1992] [Mattern et al 1989] [McGuigan 1970] [McRuer 1991] [Meckstroth and Blake 2015] [Merchant et al 2003] [Mihaloew 1981] [Momiyama 1977] [Muller and Wesshaar 1994] [Myers 1984] [Neighbors and Rock 1993] [Neighbors and Rock 1994] [Nguyen 2026] [O’Brien and Lowe 2015] [Ochi and Kanai 2001] [Orhan and Subbarao 2021] [Page and Steinberg 1999] [Pakmehr et al 2017] [Papadales and Basil S. 1979] [Park et al 2019] [Payne 1967] [Pei et al 2018] [Peng and Zhang 2017] [Pfeifle and Fichter 2021] [Pfeifle and Fichter 2023] [Postlethwaite 1997] [Postlethwaite and Bates 1998] [Potthast 1982] [Prochazka et al 2018] [Propulsion control system designs for advanced Navy multimission aircraft 1990] [Prudhomme and Haj-Hariri 1994] [Qiao and Guo 2021] [Rao and Saraf 2003] [Redondo Gutierrez et al 2022] [Resta et al 2021] [Reukauf et al 1975] [Reukauf and Burcham 1976] [Rock 1989] [Rock 1991] [Rock et al 1988] [Rock et al 1994] [Romeu 2018] [Rosenberg 1988] [Rüddenklau and Schitter 2026] [Samimy et al 2011] [Santos et al 2022] [Scalera and Durham 1999] [Schierman and Schmidt 1991] [Schierman and Schmidt 1992] [Schierman and Schmidt 1994] [Schley 1999] [Schmidt et al 1993] [Schmidt and Schierman 1990] [Scordamaglia et al 2025] [Seitz 1975] [Semiletov and Karabasov 2016] [Sevich and Beattie 1974] [Shaw et al 1987] [Shearwood et al 2020] [Shebl 2026] [Shevchenko and Pavlov 2018] [Shevchenko et al 2017] [Shevchenko et al 2019] [Shmilovich and Yadlin 2020] [Shuo et al 2025] [Sisson and Dogan 2025] [Sisson et al 2024] [Skira et al 1980] [Smith and Meyer 1981] [Smith et al 1991] [Solnyshkin 2024] [Soufivand et al 2024] [Spaans et al 2024] [Stam and de Visser 2025] [Stewart 1992] [Stewart et al 1992] [Stortz and O’Donoghue 1993] [Su et al 2022] [Sun et al 2015] [Sun et al 2026] [Surmann et al 2024] [Swortzel and Barfield 1976] [Tanveer and Ahmad 2023] [Teel 1999] [Teel 1999] [The Integrated Flight and Powerplant Control System Demonstration programme 1993] [Theilliol et al 2015] [Tillman and Ikeler 1991] [Tohidi and Yildiz 2021] [Tohidi et al 2017] [Tohidi et al 2018] [Tohidi et al 2021] [Troudet et al 1991] [Tudosie 2017] [Tudosie 2017] [Turner et al 2001] [VanSchalkwyk et al 2001] [Vernyi et al 2026] [Vile et al 2019] [Vile et al 2019] [Vile et al 2020] [Vinayagam and Sinha 2023] [Vizzini 1985] [Wang and Wang 2020] [Wang et al 2021] [Wang et al 2023] [Wang Fawei 2016] [Warsop et al 2019] [Weinstein et al 1986] [Wells 2002] [Williams and Vittal 2002] [Wise et al 1999] [Witkowska and Śmierzchalski 2018] [Wu et al 2025] [Wu et al 2026] [Xiang et al 2025] [Xu and Zha 2020] [Xu et al 2017] [Xue and Atkins 2003] [Yang and Gao 2020] [Yang et al 2025] [Yi et al 1979] [Yiming et al 2019] [Yin et al 2019] [Yonke et al 1985] [Younes and Hickey 2020] [Yu et al 2022] [Yu Luo et al 2004] [Yuan et al 2023] [Zein-Sabatto et al 2017] [Zhang et al 2015] [Zhang et al 2020] [Zhang et al 2025] [Zhao et al 2020] [Zhou and Xin 2020]
Jet impingement, ground effect and hot gas ingestion
Jet impingement on surfaces, ground effect, fountains, outwash, hot gas ingestion and the jet footprint, with the flow and heat transfer of a free gas jet on a plate, which is the physics of deck heating. Of these records, 205 were published in 2001 or earlier, and 88 in 2015 or later.
318 records. [Afroz and Sharif 2020] [Aillaud et al 2016] [Aillaud et al 2017] [Akashi et al 1996] [Allen 2004] [Amuedo et al 1989] [Antošová and Trávníček 2022] [Arledge et al 1996] [Askari et al 2018] [Baban et al 1990] [Balakrishnan and Srinivasan 2016] [Barata 1991] [Barata et al 1993] [Barron and An 1996] [Batther et al 2026] [Bauer 1987] [Beatty and Riccius 1983] [Beaubert and Viazzo 2002] [Behrouzi and McGuirk 1999] [Behrouzi and McGuirk 2000] [Behrouzi and McGuirk 2000] [Berman and Andersen 1996] [Bernard et al 2000] [Bhagwat and Sridharan 2016] [Bilen and Yavuz 2023] [Blake and Laughrey 1987] [Bolanovich and Marks 1959] [Bray and Knowles 1989] [Bray and Knowles 1990] [Brehm et al 2015] [Brehm et al 2017] [Bruschewski et al 2025] [Cai and He 2017] [Cai et al 2017] [Campbell et al 1977] [Campbell et al 1978] [Castells and Mishler 1973] [Catalano et al 1977] [Chaderjian et al 2002] [Chaderjian et al 2002] [Chakraborty et al 1990] [Chien 1975] [Childs 1991] [Childs et al 1987] [Childs et al 1992] [Chilukuri 2020] [Cimbala et al 1987] [Cimbala et al 1988] [Compton and Bowers 1983] [Cosgrove and Ryan 1969] [Cosgrove et al 1968] [Crafton et al 1999] [Crafton et al 2017] [Crowell and Myers 2016] [Curtis 2002] [Curtis and Penrose 1993] [Davanlou et al 2026] [Davidson et al 1972] [Dennis et al 1993] [Design concepts for minimizing hot-gas ingestion in V/STOL aircraft 1981] [Dhruw et al 2022] [Donaldson et al 1966] [Donaldson et al 1971] [Dosanjh and Montegani 1968] [Dudley et al 1981] [Echigo et al 2019] [Editor 2016] [El-Okda and Telionis 2002] [Eshlemen 1985] [Eyles et al 2002] [Fanucci et al 1969] [Farzad and Yagoobi 2019] [Fink and Lastinger 1961] [Fluk 1981] [Fluk and Wu 1983] [Fogleman et al 2026] [Foltz 1962] [Foss 1979] [Foss and Kleis 1976] [Fricker et al 1992] [Gao et al 2018] [Gao et al 2019] [Garcia et al 2026] [George et al 1964] [Goericke et al 2024] [Gratzer and Mahal 1972] [Greene 2020] [Grossman 1963] [Gudi and Hindasageri 2021] [Gutmark et al 1978] [Hall 1970] [Hange and Wardwell 1992] [Hange and Wardwell 1993] [Hattori and Nagano 2004] [Haviland and Herling 1977] [He and Liu 2018] [He et al 2024] [Hong and Jeon 1994] [Hong and Lee 2002] [Hot gas ingestion and the speed needed to avoid ingestion for transport type STO/VL and STOL configurations 1984] [Hromisin et al 2015] [Hsiao et al 2004] [Hsu et al 2025] [Hu and Christopher 2018] [Huang and Macinnes 1988] [Huang et al 2024] [Huggett 1959] [Humbert et al 2021] [Hung and Lin 1994] [Hwang 1988] [Hwang 1990] [Hwang and Tsou 1981] [Hyun 1996] [Ing and Zhang 1993] [Ing and Zhang 1994] [Ing et al 2002] [Ison 2024] [Issa et al 2016] [Issac et al 2019] [Iwasa et al 2018] [Jackson and House 1982] [Jalabert and Bellan 2024] [Jambunathan et al 1992] [Johns et al 1988] [Johns et al 1989] [Johns 1989] [Johns et al 1989] [Johns et al 1990] [Johns et al 1990] [Joshi and Compton 1985] [Kaemming and Smith 1984] [Kaewbumrung and Plengsa-Ard 2023] [Kaewchoothong 2025] [Kamman and Hall 1978] [Kamman et al 1979] [Kashimura et al 1999] [Kataoka et al 1982] [Khader 1971] [Khalaji et al 2015] [Kim and Park 2003] [Kirk and Barrack 1969] [Klestov 1978] [Knott 1987] [Kopaç 2002] [Kotansky 1978] [Kotansky and Glaze 1981] [Kotansky 1982] [Krishnamoorthy 1971] [Kristy 1995] [Krothapalli 1983] [Krothapalli et al 2003] [Kuhlman and Warcup 1977] [Kuhlman and Warcup 1978] [Kuhlman and Warcup 1980] [Kuhlman and Warcup 1979] [Kuhn et al 1993] [Kuhn et al 1993] [Kumada and Mabuchi 1970] [Kumar et al 1998] [Lak et al 2020] [Lake et al 2000] [Lancey and Cooper 1989] [Lee et al 2004] [Lemanov et al 2018] [Levin and Wardwell 1997] [Lewis and Hurd 1980] [Li et al 2016] [Lim and Yee 2026] [Lissaman 1967] [Lissaman 1968] [Lissaman 1969] [Liu et al 2023] [Lord 1985] [Lou et al 2003] [Maclean 1991] [Margason 2002] [Margason and Tso 1993] [Margason et al 1996] [Margason 1966] [Margason 1970] [Marsh 1961] [Maurel and Solliec 2001] [McGuirk et al 2002] [McMurray et al 2019] [Meola et al 1995] [Mezzacapo et al 2025] [Miller 1995] [Miller et al 1991] [Morse and Newhouse 1960] [Morse and Newhouse 1961] [Morse and Newhouse 1961] [Mourtos et al 1995] [Murai et al 1984] [Murman et al 2001] [Myszko and Knowles 1994] [Narayanan 2003] [Natarajan and Venkatakrishnan 2019] [Nichols et al 2025] [Land and Clark 1965] [Norum 1989] [Nosseir and Ho 1980] [Nosseir and Peled 1986] [Nosseir et al 1987] [Numerical Investigation Of Three Dimensional Laminar Jet Impingement On Heated Plate Surface 2016] [O’Bryan 1961] [Oved and Haustein 2023] [Oved et al 2024] [Pamadi 1980] [Park and Sung 2001] [Penrose and Smith 1996] [Petrie 1980] [Pham Van Bang et al 2022] [Polat et al 1985] [Qi et al 2001] [Radzman and Uddin 2018] [Rajendiran Vijayaraj et al 2025] [Rathakrishnan 2024] [Reda et al 1997] [Renselaer 1975] [Rim et al 2016] [Robinson 1978] [Robinson and High 1974] [Rogers and Belluomini 2026] [Rubel 1978] [Rubel 1978] [Rubel 1982] [Ryan 1966] [Rönnberg and Duwig 2021] [Saddington et al 2002] [Saddington et al 2008] [Saddington et al 2009] [Saini et al 2022] [Sakakibara et al 2001] [Samantaray and Arumuru 2025] [Sandoval and Zhang 2026] [Sarangi and Srinivasan 2022] [Saripalli 1981] [Saripalli 1983] [Saripalli 1985] [Saripalli et al 1997] [Schnell and Grossman 1978] [Schnell 1982] [Scholtz and Trass 1970] [Schuster and Flood 1978] [Seiner et al 1988] [Sementi 2002] [Sharif 2015] [Sharma et al 2020] [Sharma et al 2021] [Sheplak and Spina 1993] [Shi et al 2002] [Shishir et al 2001] [Shivdas et al 2019] [Siba et al 1998] [Sibulkin 1964] [Siclari et al 1975] [Siclari et al 1976] [Siclari et al 1977] [Simmons et al 2023] [Singh 2022] [Smith et al 1993] [Smith et al 1993] [Smith et al 1994] [Soltis and Sangeorzan 2015] [Sparrow and Lee 1975] [Sparrow et al 1975] [Stapountzis 1993] [Stewart and Blake 1992] [Stewart and Blake 1993] [Strand 1967] [Striegl and Diller 1984] [Striegl and Diller 1984] [Sullivan and Murthy 1990] [Tafti and Vanka 1990] [Taghinia and Rahman 2018] [Tan et al 2018] [Tawfek 1996] [Tchavdarov 1997] [The normal impingement of a circular air jet on a flat surface 1962] [Tibabisco et al 2019] [Tsuboi et al 1991] [Tsubokura et al 1998] [Tu and Wood 1996] [Saranyamol et al 2026] [Vanka 1998] [Vanoverbeke and Holdeman 1988] [VanOverbeke and Holdeman 1990] [Vinay et al 2022] [Von Glahn and Groesbeck 1979] [Wachspress et al 2026] [Walker 1964] [Wang et al 2026] [Ward and Mahmood 1982] [Wardwell and Hange 1993] [Wardwell et al 1992] [Wardwell et al 1993] [Wareing 1968] [Weber and Williams 1978] [Weightman et al 2016] [Wen et al 2016] [Wernicke 1981] [White et al 1960] [Wichita State Univ Ks 1962] [Winston et al 1975] [Wohllebe and Migdal 1979] [Wolfshtein 1970] [Worden et al 2016] [Wright and Seitz 2019] [Wu et al 2001] [Yeh et al 1993] [Yen 1981] [Yon and Li 2026] [Yoshihara 1963] [Zhang and Agarwal 2020] [Zhang and Ibrahim 2004] [Zhang and Ing 1993] [Zhang and Ing 1994] [Zhang et al 2019]
Electric, distributed and hybrid propulsion and electric vertical takeoff
Electric, hybrid and distributed propulsion, electric vertical-takeoff aircraft and the aircraft-level design of their powertrains. Of these records, 9 were published in 2001 or earlier, and 415 in 2015 or later.
434 records. [Abergo et al 2026] [Abryandoko et al 2026] [Ahuja et al 2026] [Aktas 2015] [Algorithm for selecting UAV’s electric propulsion system parameters based on flight route 2015] [Allenspach and Ducard 2021] [Amping Airpower-Electric Vertical Takeoff 2024] [Anantha et al 2024] [Anderson et al 2024] [Arias et al 2025] [Arias et al 2025] [Avant et al 2018] [Awad and Stumpf 2022] [Aydin et al 2025] [Babčan and Janovec 2021] [Bahr et al 2021] [Bai et al 2024] [Bandopadhyay and Mistry 2019] [Bandopadhyay and Mistry 2022] [Barra et al 2020] [Barry et al 2023] [Beals et al 2026] [Bendarkar et al 2021] [Simmons 2023] [Benmoussa and Gamboa 2023] [Benyamen and Keshmiri 2022] [Beschorner et al 2025] [Bezerra and Santos 2022] [Bhandari and Chakraborty 2026] [Bhandari et al 2023] [Bhandari et al 2024] [Bonnin and Hoogreef 2025] [Bonnin et al 2023] [Borer et al 2017] [Boretti 2023] [Boretti 2024] [Bowman et al 2018] [Bravo et al 2021] [Brelje and Martins 2018] [Brenner et al 2023] [Britcher and Baris 2023] [Brown and Hagen 2017] [Cai et al 2023] [Cao et al 2024] [Caudle et al 2025] [Centracchio et al 2018] [Chakraborty 2019] [Chakraborty and Mishra 2022] [Chakraborty and Mishra 2023] [Chakraborty and Mishra 2023] [Chana 2002] [Chang et al 2022] [Chapman 2023] [Chauhan and Martins 2020] [Chen et al 2023] [Chen et al 2025] [Cheng et al 2025] [Choi et al 2025] [Choi et al 2026] [Chopra et al 2022] [Comunian et al 2025] [Connolly et al 2018] [Cook and Hauser 2018] [Courtin and Hansman 2019] [Cunningham et al 2022] [Cusanelli and Slutsky 2008] [Cusati et al 2023] [Dang 2026] [Dantsker et al 2018] [Dantsker et al 2019] [Darmstadt et al 2021] [De Lucena et al 2022] [de Rosa et al 2022] [de Vries and Vos 2022] [de Vries et al 2019] [Dean et al 2018] [Deere et al 2017] [Dela Peña 2025] [Deng et al 2024] [Derrouaoui et al 2023] [Diaz et al 2019] [Diecke 2023] [DiMaggio et al 2025] [Ding et al 2025] [Dowdle et al 2018] [Duan et al 2024] [Dubois et al 2016] [Ducard and Carughi 2024] [Duffy and Jansen 2018] [Dukhnovskiy 2023] [Dunaevskii et al 2020] [Dyson 2018] [Dyson 2023] [Ebus and Dietz 2020] [Economou et al 2019] [Elahi Kahooker and Liu 2026] [Elbasueny et al 2019] [Elbir and Üçgül 2026] [Enenakpogbe et al 2024] [Fardin et al 2026] [Farsi and Rosen 2023] [Feroskhan et al 2025] [Figueira et al 2025] [Filippoli 2026] [Finger et al 2018] [Finger et al 2020] [Finger et al 2020] [Firnhaber Beckers et al 2023] [Flanagan and Jarrett 2023] [Flight Test Data Analysis of Hybrid Vertical Take-off and Landing Unmanned Aerial Vehicle 2016] [Frederick et al 2021] [Fredericks et al 2013] [Freeman and Klunk 2018] [Friedrich and Robertson 2015] [Fulton et al 2026] [Gallani et al 2020] [Gebril and Kamal 2023] [Geisbert and Schroeder 2008] [Gelhausen and Wilson 1986] [Gkoutzamanis et al 2020] [Goldberg et al 2016] [Gonzalez et al 2026] [Guner 2022] [Guo et al 2023] [Ha et al 2020] [Habermann 2020] [Hallez et al 2018] [Hartman et al 2025] [Hashem Dabaghian and Halder 2025] [He 2024] [He et al 2020] [He et al 2026] [Hein and Myschik 2022] [Herbst et al 2015] [Herzog et al 2021] [Herzog et al 2024] [Hirschkron et al 1979] [Hoffman et al 2017] [Hoffman et al 2018] [Hsu et al 2023] [Hu and Booker 2022] [Hu et al 2026] [Huang 2023] [Huang et al 2020] [Hyun et al 2023] [Imani and Anjomrouz 2025] [Ingraham and Falck 2025] [Isikveren 2018] [Jacobson and Smith 2018] [Jansen et al 2017] [Jansen et al 2019] [Jayasundara and Baeder 2023] [Jeong et al 2024] [Jiang and Pakmehr 2022] [Jiang et al 2022] [Doo et al 2021] [Johnson and Silva 2026] [Johnson et al 2024] [Jois et al 2024] [Litt et al 2026] [Juvé et al 2016] [Kadhiresan and Duffy 2019] [Kamath et al 2025] [Kaneshige et al 2023] [Kang et al 2023] [Kang et al 2025] [Kang et al 2025] [Kannan et al 2025] [Karemaa 1971] [Katagiri et al 2025] [Kaushik et al 2025] [Keller 2021] [Keller 2023] [Keller 2025] [Keller et al 2024] [Kerho 2015] [Kim et al 2018] [Kim et al 2008] [Kirner et al 2015] [Klunk and Freeman 2018] [Kohout 2003] [Kohout 2004] [Kohout and Schmitz 2003] [Koshel et al 2026] [Kotaru et al 2019] [Kou et al 2021] [Kozakiewicz and Grzegorczyk 2021] [Kramer et al 2024] [Kruger and Uranga 2020] [Kruger and Uranga 2024] [Kunwar and Chakraborty 2025] [Kuzniar et al 2020] [Lammen et al 2025] [Lampl and Armanini 2023] [Laskaridis 2015] [Lechniak et al 2020] [Lee and Park 2022] [Lee and Yee 2024] [Lee et al 2022] [Lee et al 2024] [Lee et al 2026] [Legrand et al 2024] [Legrand et al 2025] [Lei and Zhao 2023] [Lemelin et al 2026] [Machado et al 2025] [Li et al 2017] [Li et al 2021] [Li et al 2022] [Li et al 2024] [Li et al 2026] [Libório et al 2025] [Lindner et al 2023] [Litt 2026] [Liu and Tan 2024] [Liu and Wang 2024] [Liu et al 2022] [Liu et al 2023] [Liu et al 2024] [Liu et al 2025] [Liu et al 2026] [Love 2022] [Lykyanov and Adler 2023] [Lympany and Page 2024] [Lück et al 2025] [Ma et al 2020] [Ma et al 2022] [Maadani et al 2023] [Macit and Özer 2025] [Magata et al 2025] [Mahvelatishamsabadi and Emadi 2020] [Majka and Muszyńska-Pałys 2023] [Mak et al 2023] [Malpica et al 2024] [Mao et al 2022] [Marepally et al 2025] [Marksel and Prapotnik Brdnik 2022] [Martin 2025] [Martinez et al 2025] [Mathur and Atkins 2026] [May et al 2022] [May et al 2023] [May et al 2025] [McCrink and Gregory 2015] [McCrink and Gregory 2017] [McDonald 2015] [McDonald 2016] [Michalík and Čerňan 2020] [Mieloszyk and Tarnowski 2019] [Min et al 2026] [Minervino et al 2022] [Misiorowski et al 2019] [Mohammadi et al 2023] [Moore and Ning 2019] [Moore 2010] [Morani et al 2024] [Mukherjee et al 2023] [Murphy and Landman 2015] [Nakka and Alexander-Ramos 2021] [Blaesser et al 2024] [Neogi et al 2025] [Ng and Datta 2018] [Ng and Datta 2019] [Nguyen and Webb 2025] [Nguyen and Xiong 2026] [Nguyen et al 2018] [Nguyen et al 2023] [Nguyen et al 2025] [Ni and Lee 2025] [Nicolay et al 2021] [Nicolosi et al 2022] [Zawodny et al 2022] [Nishikawa and Rinoie 2024] [Nisi and Tang 2025] [North et al 2021] [Okai et al 2015] [Okai et al 2020] [Oki et al 2002] [Oldeweme et al 2024] [Oliinyk and Zylevich 2026] [Orefice et al 2019] [Orefice et al 2020] [Orrick 2024] [Osman et al 2026] [Oumlik and Dai 2026] [Panish and Bacic 2025] [Park 2025] [Park et al 2025] [Park et al 2025] [Pascioni et al 2026] [Pařez et al 2025] [Peng et al 2018] [Perry et al 2018] [Perry et al 2021] [Pfeifle et al 2021] [Pieper et al 2018] [Poggi et al 2024] [Pontika et al 2023] [Portapas 2025] [Posnett et al 1986] [Posnett et al 1987] [Pratt and Cadou 2026] [Prochazka and Stomberg 2020] [Qin et al 2023] [Quillet et al 2023] [Riboldi and Gualdoni 2016] [Riboldi et al 2018] [Ricci et al 2020] [Roiati et al 2023] [Ruggeri et al 2017] [Russo et al 2023] [Saberi et al 2026] [Sachs et al 2022] [Sadiq Ali Mir et al 2025] [Saetti et al 2020] [Saha et al 2026] [Salahudden et al 2023] [Salucci et al 2021] [Samuel and Lin 2015] [Sarikaya et al 2026] [Sarup 2026] [Satria Palar et al 2024] [Savino and Zanotti 2025] [Scholz et al 2021] [Scholz et al 2022] [Schroeter et al 2024] [Senthil Kumar et al 2018] [Seo et al 2020] [Seo et al 2021] [Sharpe and Agarwal 2019] [Sheng and Zhao 2025] [Sheng and Zhao 2026] [Shi et al 2024] [Shinozuka et al 2024] [Shubert and Sizoo 2025] [Siddavatam et al 2023] [Whiteside et al 2021] [Simmons 2022] [Simmons 2023] [Simmons and Murphy 2021] [Simmons and Murphy 2022] [Simmons et al 2021] [Smith 1958] [Smith 1961] [Snyder 2020] [Song and Sun 2017] [Sorensen et al 2024] [Spadão et al 2026] [Spannagl and Ducard 2020] [Stahl et al 2018] [Staruk et al 2020] [Stewart et al 2026] [Strathoff et al 2020] [Su and Rauleder 2026] [Suiçmez and Kutay 2023] [Sullivan and Hager 1983] [Sun and de Visser 2019] [Susilo et al 2024] [Synodinos et al 2018] [Synodinos et al 2024] [Taflan et al 2024] [Tariq and Nahon 2020] [Tatenda and Qiang 2023] [Throneberry et al 2022] [Traub 2016] [Tumelero Valente et al 2023] [Upadhyay and Zaman 2019] [Valencia et al 2019] [Vegh 2025] [Vepa 2021] [Waddington et al 2023] [Wahler et al 2023] [Wahler et al 2025] [Wall and Meyer 2017] [Wall and Meyer 2020] [Walter et al 2023] [Walter et al 2023] [Walvekar and Chakravarthy 2022] [Walvekar and Chakravarthy 2023] [Wang 2026] [Wang and Hu 2026] [Wang and Mesbahi 2021] [Wang and Zhang 2022] [Wang et al 2021] [Wang et al 2023] [Wang et al 2023] [Wang et al 2023] [Wang et al 2024] [Wang et al 2024] [Wang et al 2025] [Wang et al 2025] [Wang et al 2026] [Ward and Penrose 1983] [Waters et al 2015] [Wei et al 2021] [Wei et al 2024] [Wei et al 2026] [Wen et al 2020] [Westcott et al 2025] [Wheeler et al 2021] [Willis and Beard 2022] [Wroblewski and Ansell 2018] [Wroblewski and Ansell 2020] [Wu et al 2023] [Wu et al 2025] [Wu et al 2026] [Xiao et al 2024] [Xie et al 2023] [Xie et al 2026] [Xu et al 2025] [Xue et al 2026] [Yang and Morales 2021] [Yang and Tan 2025] [Yang et al 2023] [Yang et al 2024] [Yokota and Fujimoto 2022] [You et al 2026] [Yu et al 2021] [Yılmaz and German 2024] [Zaki et al 2017] [Zaludin 2024] [Zaludin and Harituddin 2019] [Zanotti and Algarotti 2022] [Zanotti et al 2024] [Zhang et al 2021] [Zhang et al 2023] [Zhao et al 2023] [Zhao et al 2024] [Zhao et al 2025] [Zhao et al 2025] [Zheng et al 2025] [Zistler et al 2025] [Zou 2022] [Łukasik 2017]
Rotors, propellers, actuator discs and momentum theory
Rotors and propellers, the actuator disc, blade element and momentum theory, and rotor wakes, in hover and forward flight. Of these records, 175 were published in 2001 or earlier, and 206 in 2015 or later.
400 records. [Aa. Madsen 2024] [Abras and Hariharan 2018] [Agarwal and Deese 1986] [Aggarwal 1986] [Ahuja and Litherland 2023] [Ai et al 2018] [Amin and Aijun 2017] [Andersson et al 2026] [Andrejczyk 2023] [Arias et al 2021] [Asiatico et al 2026] [Açıkgöz and Aslan 2016] [Bachelder et al 2002] [Bagai and Leishman 1992] [Balch 1985] [Ballard et al 1980] [Barakos et al 2020] [Beals 2018] [Beaumier et al 2001] [Bennett 1984] [Benser et al 1975] [Berry 1982] [Beveridge 1974] [Bingham and Noonan 1975] [Block et al 1986] [Bludau et al 2017] [Bohorquez and Pines 2003] [Boldman et al 1991] [Bolin et al 2015] [Bolt 1980] [Bossler and Robert B. 1965] [Boulkeraa et al 2022] [Bowden and Shockey 1970] [Brahma Nand Agrawal et al 2024] [Breton et al 2017] [Buffum and Robertson 1967] [Burger et al 1975] [Busch et al 2015] [Cameron et al 2016] [Cao 1999] [Cao and Su 2003] [Cao et al 2023] [Cao et al 2024] [Carreno Ruiz et al 2024] [Cerbe and Reichert 1989] [Cha and Kinnas 2022] [Chaderjian 2022] [Chapman et al 2025] [Chattopadhyay et al 1992] [Chen and Hubner 2020] [Chen et al 2026] [Chen 1992] [Cherrett et al 1994] [Cherrett et al 1995] [Chidambaram and Vinoth Raj 2025] [Chinwicharnam et al 2015] [Chiocchia and Pignataro 1995] [Choi et al 2025] [Coleman et al 1996] [Cormier 1979] [Cornelius et al 2021] [Coward 1955] [Crimi 1965] [Culpepper et al 2021] [Cybyk et al 1995] [Cyrus 1998] [Darlow and Vance 1974] [Davenport et al 1985] [de Souza and Ciloni 2021] [Degang and Xiang 2020] [Delorme et al 2021] [Derakhshan et al 2024] [Dias et al 2025] [Doblhoff 1956] [Dodic et al 2023] [Dutton 1967] [Editor 2016] [Eick and Liu 1996] [Ellenrieder and Brinson 1998] [Erwin and Vitale 1972] [Evangelista et al 2023] [Fan et al 2020] [Feil et al 2016] [Feil et al 2019] [Felker and Light 1988] [Ferrar et al 2016] [Flax 1995] [Fourie and Jones 2015] [Fox et al 1974] [Fradenburgh et al 1973] [Fredrickson et al 1972] [Frohnapfel et al 2017] [Frohnapfel et al 2017] [Fujiwara et al 2026] [Fulton and Ormiston 2001] [Gao et al 2017] [Garcia et al 2009] [Gennaretti et al 2016] [Gennaretti et al 2023] [Ghareeb 1964] [Gill and Lee 2025] [Godston and Reynolds 1983] [Gorrell et al 2001] [Grava et al 2026] [Gray et al 1953] [Gu et al 2016] [Guner et al 2019] [Gustafson 1962] [Habib et al 2018] [Halder and Benedict 2018] [Han et al 2017] [Hansen 2023] [Hariharan et al 2015] [Harris 1999] [Harun-Or-Rashid et al 2015] [Hasan et al 2022] [Hashem Dabaghian et al 2025] [Hazen and Seckel 1950] [He et al 2026] [Heimerl and Benedict 2022] [Hermes and Wood 1969] [Hess et al 2026] [Heyson and Katzoff 1956] [Heyson and Katzoff 1957] [Hill 1975] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hodges et al 1988] [Huang et al 2015] [Hughes et al 2002] [Ichikawa et al 2020] [Iseni et al 2016] [Jacobellis and Gandhi 2016] [Jain 2017] [Jain 2018] [Jain 2018] [Jenkins and Marks 1975] [Jeong and Cho 2026] [Ji and Xie 2023] [Jia and Lee 2020] [Jia and Lee 2021] [Jia et al 2018] [Jiang et al 2018] [Jimenez Garcia and Barakos 2018] [Jo et al 2017] [Johnson and Sirohi 2024] [Johnson et al 2024] [Johnson et al 2007] [Johnston and Fleeter 2004] [Joseph and Badrya 2026] [Jung et al 2026] [Jung et al 2026] [Kaman Aircraft Corp Bloomfield Ct 1964] [Kang and Kwon 2001] [Kato and Yamane 1979] [Kato et al 1981] [Kawachi 1982] [Kim 2016] [Kim and Stern 1990] [Kimura et al 2022] [Kimura et al 2023] [Kitaplioglu 1986] [Kitaplioglu and Kinney 1986] [Klimchenko et al 2023] [Kodama and Namba 1992] [Komerath et al 1985] [Komerath et al 1988] [Kong et al 2004] [Koratkar and Chopra 2001] [Kos et al 1973] [Kovich and Moore 1976] [Kozak et al 2019] [Ku and Sankar 2026] [Kuntz 1996] [Kusunose et al 2000] [Lai and Le Tri 2017] [Lakshminarayana and Popovski 1986] [Lamar 2004] [Landgrebe 1971] [Le Chuiton 2004] [Lee and Dassonville 2019] [Lee and Kim 1993] [Lee and Yee 2016] [Lee et al 2021] [Leese 1964] [Leese 1972] [Leese and Knight 1974] [Lepicovsky and Bell 1983] [Lesieutre and Sullivan 1986] [Li et al 2017] [Li et al 2020] [Li et al 2023] [Lim et al 2026] [Lindblad et al 2018] [Liu 2002] [Liu et al 2024] [Lu et al 2022] [Akash et al 2023] [Ma et al 2017] [Magliozzi 1987] [Magrini 2022] [Mahmuddin 2017] [Malick and Agarwal 2015] [Martin et al 1999] [Mathioudakis 1985] [Maurya et al 2021] [Maurya et al 2023] [McDonnell Aircraft Corp St Louis Mo 1950] [Meakin 1995] [Mehta et al 2015] [Mihaloew et al 1988] [Mihaloew et al 1988] [Miller 1983] [Molyneux 1983] [Montero Villar et al 2018] [Moore et al 2026] [Moore and Reid 1982] [Moreau et al 2024] [Mortimer et al 2023] [Morton 1983] [Müller et al 1996] [Nagel and Patrick 1988] [Nallasamy 1993] [Nallasamy et al 1988] [Nederlof et al 2023] [Neuhoff 1985] [Nicholson and Moore 1986] [Nishimura et al 2023] [Nordquist et al 1972] [Norton et al 1979] [Nunez Garcia et al 2026] [O’Brien and Datta 2026] [Ockier and Celi 1991] [Oliva and Morris 2022] [Osborn and Hager 1976] [Overmeyer and Martin 2017] [Overmeyer and Martin 2017] [Padthe et al 2022] [Page et al 2017] [Park et al 2026] [Parker and Simonson 1982] [Parker and Simonson 1982] [Parker and Simonson 1982] [Parzych 1990] [Parzych and Shattuck 1986] [Passe et al 2015] [Patil and Datta 2024] [Paxson 1996] [Pereyra and Kung 2026] [Peterson and Warmbrodt 1986] [Peyton Autry 1946] [Podsędkowski et al 2023] [Pomin and Wagner 2001] [Prasad 2025] [Prato and Lakshminarayana 1992] [Propeller Slipstream Effects on the Aerodynamics Characteristics of a Transition Micro Air Vehicle 2025] [Prothin and Doué 2015] [Prouty 1975] [Qi et al 2022] [Qi et al 2024] [Qiu 2025] [Quackenbush et al 1989] [Quackenbush et al 1991] [Quackenbush et al 2019] [Quackenbush et al 2020] [Rajagopalan 1988] [Rajagopalan and Lim 1991] [Rajmohan et al 2015] [Ramachandran et al 1989] [Ramachandran et al 1989] [Ramanujam and Abhishek 2022] [Rand and Khromov 2017] [Rao and Schatzle 1978] [Reid and Moore 1978] [Richardson and Liiva 1970] [Rinehart 1970] [Roberts et al 2002] [Roberts et al 2005] [Rock and Neighbors 1994] [Rohrbach and Wainauski 1981] [Rosen 2004] [Rosen 2004] [Rossow 1985] [Rostami and Farajollahi 2021] [Rubinstein 2014] [Runco et al 2019] [Ruttledge 1986] [Samanich and Heidelberg 1976] [Samant et al 1983] [Sambell 1971] [Sanderson and Holly 1993] [Sankar and Komerath 1988] [Schleicher et al 1993] [Schmitz 1971] [Schmitz and Vause 1976] [Schroers and Antoniou 1964] [Schröder and Schuster 1972] [Seidel and Peters 2019] [Shah and Bilgen 2023] [Shahmiri 2017] [Sheng 2018] [Sheng et al 2016] [Sheng et al 2018] [Shenoy and Gray 1981] [Shipman and Bin 2021] [Shivananda et al 1978] [Shivashankara et al 1990] [Shivers 1961] [Shrestha et al 2016] [Shukla et al 2022] [Simon and Bohn 1974] [Simulation of Rotor-Rotor Interaction and Noise of an Axial Counter-Rotating Fan 2023] [Singh and Friedmann 2018] [Sitaram 1988] [Smith 1968] [Smith et al 2026] [Son and Kim 2023] [Sorensen and Cuppoletti 2022] [Sorensen and Cuppoletti 2022] [Spencer et al 1969] [Srinathkumar 2019] [Srinivasan and McCroskey 1988] [Stanly et al 2020] [Stevens et al 2015] [Stoll and Veble Mikić 2022] [Strawn and Djomehri 2002] [Strazisar et al 1989] [Swanson 1993] [Takallu and Gentry 1992] [Tan et al 2018] [Taniguchi and Oyama 2022] [Taymourtash et al 2021] [Taymourtash et al 2021] [Thompson et al 1988] [Toha et al 2015] [Uehara et al 2019] [van Kuik et al 2015] [Velkoff et al 1971] [Vella et al 2026] [Vitale et al 2023] [Vogeley 1948] [Volkov et al 2022] [Vu and Lee 2015] [Waanders and Rauleder 2026] [Wadia and Law 1992] [Wadia et al 2018] [Wainauski and Vaczy 1986] [Wallace et al 2025] [Walsh et al 2016] [Wang 2003] [Wang and Jin 2025] [Wang et al 2007] [Wang et al 2020] [Wang et al 2021] [Wang et al 2022] [Warmbrodt and Hull 1982] [Warsett 1953] [Webster et al 1995] [Wei and Zhong 1988] [Weilenmann and Geering 1993] [Wennerstrom and Frost 1974] [Westcott et al 2023] [Whitehead 1986] [Whitehead and Davies 1983] [Williams and Bernitt 1970] [Willshire and Martin 1984] [Wood 2001] [Wood and Hammam 2022] [Woodward 1992] [Woodward and Glaser 1976] [Wright and Silva 2026] [Wu et al 2021] [Wu et al 2024] [Xie and Haberland 1999] [Xue et al 2024] [Yang and Zhuang 2000] [Yang et al 2026] [Yao and Li 2024] [Ye et al 2024] [Yeh 1959] [Yeo and Johnson 2015] [Yin 2019] [Yoshida et al 2021] [Yuan et al 2024] [Yurt et al 2026] [Zhang and Liu 2024] [Zhang et al 2019] [Zhang et al 2025] [Zhao 2018] [Zhao and Li 2018] [Zhao and Wang 2016] [Zhao et al 2025] [Zhu and Zhao 2015] [Zoppelt et al 2024] [Öhrle et al 2019] [Šajbanová and Čerňan 2021] [Šajbanová et al 2021]
Transonic and supersonic drag
Transonic and supersonic drag, wave drag, shock interaction and the aerodynamics of the speed range the dash crossed. Of these records, 93 were published in 2001 or earlier, and 49 in 2015 or later.
151 records. [A Prediction Method for Deck Motion of Aircraft Carrier Based on Particle Swarm Optimization and Kernel Extreme Learning Machine 2017] [Abdol-Hamid et al 2018] [Abe 2023] [Abraham et al 2023] [Ageev and Pavlenko 2016] [Agrell and Elmeland 1984] [Aidala 1985] [Andrew and Cahn 1967] [Arabshahi and Whitfield 1995] [Axelson 1975] [Baals et al 1970] [Bailey and Starr 1976] [Balusamy et al 2024] [Bergman 1948] [Bernstein 1997] [Biot 1949] [Boelens 2017] [Boppe 1978] [Boppe and Aidala 1980] [Brower 1989] [Bryson 1971] [Bushnell 1990] [Capone et al 1984] [Cartieri et al 2018] [Chadsey and Yechout 2001] [Chamberlain 1968] [Chao and van Dam 2004] [Chaparro et al 2016] [Chaussee 1978] [Chung 2004] [Coder et al 2017] [Coder et al 2018] [Cole 1988] [Cosenza and Kummeth 1974] [Coustols et al 1997] [Crites et al 1992] [de Paula et al 2017] [Derlaga and Morrison 2017] [Derlaga and Morrison 2018] [Desai et al 1977] [Dixon and Hunsaker 2023] [Doherty et al 2018] [Dollyhigh 1970] [Eminton and Lord 1956] [Esquieu 2003] [Fan and Li 2019] [Fletcher and Burns 1979] [Flores et al 1988] [Florio et al 2019] [Fournis 2022] [Fuhs 1971] [Fujino and Kawamura 2003] [Fung 1982] [Gacherieu and Weber 1998] [Gan et al 2016] [Gao 2023] [Garabedian 1976] [Gillan 1993] [Goto et al 2021] [Hinchliffe and Qin 2016] [Holdaway 1954] [Howell and Korst 1971] [Huh et al 2015] [Ito et al 2018] [Jesudasan et al 2026] [Johnson 1985] [Joshi et al 2024] [Kawasaki 1965] [Kennedy and Stuart 2025] [Keye et al 2017] [Keye et al 2023] [Khan et al 2025] [Khlebnikov 1990] [Klausmeyer 2004] [Kohn 1979] [Kondo et al 2003] [Kutney and Piszkin 1963] [König and Fares 2018] [Lee and Franz 1976] [Lee-Rausch et al 2004] [Lents 2021] [Li et al 2023] [Long 1993] [Macha 1977] [Malmuth et al 1986] [Mann and Mercer 1986] [Mason 1982] [Masson et al 1998] [Masson et al 1999] [Mavriplis and Levy 2002] [Mele et al 2017] [Mertens et al 1986] [Miles 1953] [Miles 1954] [Murman and Cole 1974] [Naida and Fonarev 1995] [Naida and Fonarev 1996] [Nelson 1986] [Newberry 1998] [Nghiem and Norstrud 1989] [Niewald and Parker 2000] [Nusrath et al 2016] [Oki et al 2000] [Page et al 2025] [Peavey 2000] [Peterson 1961] [Petruzzelli and Keane 2001] [Pittman 1987] [Prabhu et al 2025] [Price 1981] [Rajeswari and Prabhu 1987] [Ralin Bukreev 2023] [Rallabhandi and Mavris 2003] [Resulkulyeva and Serebryansky 2023] [Roach and Froning 1996] [Roth 2001] [Roy et al 2021] [Sampaio Felix et al 2023] [Sathish Kumar Sunnam et al. 2019] [Schnerr and Dohrmann 1991] [Schnerr and Dohrmann 1994] [Schwartz et al 2024] [Seider and Haenel 1991] [Shanbhag and Narasimha 1970] [Sigal 1988] [Smetana and Knepper 1973] [Smith 1997] [Sorbilli et al 2018] [Soudakov 2016] [Spearman 1979] [Squire and Nasser 1993] [Starr and Varner 1976] [Steger and Baldwin 1973] [Sun and Hansen 1982] [Supersonic flow computations for an ASTOVL aircraft configuration 1990] [Swamy et al 1978] [Takahashi 2021] [Takovitskii 2020] [van Dam et al 1995] [van der Vooren and van der Wees 1991] [Vieira et al 2025] [Viswanath 1988] [Viswanath and Rajendra 1990] [Volpe and Jameson 1990] [Walkley 1986] [Ward 1968] [Whitford 1991] [Whoric 1977] [Willhite et al 1995] [Yajnik and Subbaiah 1976] [Yu et al 1983]
Fan, compressor and counter-rotating stages
Fan and compressor stages, counter-rotating turbomachinery, stall, distortion and the stage design beneath the lift fan. Of these records, 129 were published in 2001 or earlier, and 126 in 2015 or later.
273 records. [Adjei and Fan 2024] [Advisory Group for Aerospace Research and Development 1996] [Aerodynamics of Power Plant 1981] [Ai et al 2021] [Ai et al 2025] [Alavi Moghadam et al 2017] [An et al 2025] [Ananthakrishnan et al 2019] [Andriani and Ghezzi 2002] [Aungier 1995] [Azevedo and Galdino da SIlva 2016] [Bailey 1972] [Ball 1974] [Ball 1979] [Barnhart 1989] [Barrett 1965] [Bettner and Elrod 1982] [Bohne and Niehuis 2004] [Borcherding et al 2023] [Boretti 2024] [Boyer and O’Brien 2002] [Breugelmans 1975] [Brooks et al 1976] [Bryce et al 1993] [Burger et al 1979] [Cai et al 1990] [Calvert and Stapleton 1993] [Capece and Fleeter 1984] [Carpenter and Cizmas 2017] [Carpenter and Cizmas 2017] [Chen and Zhang 1983] [Chen et al 2018] [Cherrett et al 1994] [Cherrett et al 1995] [Chima 1991] [Choe et al 2002] [Choi and Lee 2018] [Chotalia and Alone 2017] [Citavý 1992] [Cook 1976] [Copenhaver and Okiishi 1989] [Cousins and Obrien 1985] [Csank and Zinnecker 2014] [Cui et al 2025] [Cunningham and Boytos 1981] [Cunningham and Boytos 1983] [Cyrus 1990] [Dai et al 2019] [Daniels et al 1989] [Davenport et al 1974] [Davis 1972] [Dehnavi et al 2023] [Dejene Toge and Pradeep 2015] [Denton and Xu 2002] [Design Principles and Methods 1999] [Dinh and Kim 2021] [Dinh et al 2017] [Dogga and Turner 2023] [Doyle and Dixon 1962] [Druzhinin et al 2017] [Druzhinin et al 2018] [Dugas 1968] [Durali and Kerrebrock 1998] [Schwaar 1961] [Zahaby 1979] [Elliott et al 1990] [Elmendorf et al 1995] [Emmerson 1998] [Enghardt et al 2019] [Erdos et al 1976] [Ferdaus et al 2021] [Fishbach and Franciscus 1982] [Franciscus 1983] [François et al 2020] [Friedrichs et al 2000] [Fritsch et al 1997] [Frulla 2021] [Gan et al 2016] [Gao et al 2022] [Gearhart et al 1969] [Ginzburg 1976] [Girshovich 1968] [Goswami et al 2015] [Guo et al 2023] [Güllü and Aran 2023] [Hah 2015] [Hah 2010] [Hallstaff 1966] [Hao et al 2026] [Harvey and Monarch 1968] [Hasegawa et al 2018] [Haug and Niehuis 2018] [Hayami et al 2002] [Heath et al 2017] [Hiers et al 2004] [Hill 1993] [Hosotani et al 2019] [Howard and Gallimore 1992] [Howard and Puterbaugh 2016] [Howard et al 2017] [Huber et al 1993] [Huete and Singh 1997] [Hutcheson 1976] [Investigation on the inflow distortion of a propulsive fuselage aircraft and its impact on the propulsion fan performance 2023] [Isomura and Giles 1998] [Janon 2020] [Jiang et al 2015] [Johnson 1991] [Joo 2000] [Kanemoto et al 2002] [Kang et al 2017] [Kern and Hopcroft 1983] [Khader and Loewy 1989] [Khaletskii et al 2024] [Khanh Tran 2020] [Kim and Lee 2021] [Kim and You 2026] [Kim et al 2018] [King 1961] [Kofman and Becus 1996] [Konyukov 2025] [Konyukov 2026] [Kotidis and Epstein 1990] [Kovach and Sandercock 1961] [Kovich and Steinke 1976] [Kovich et al 1977] [Kozlak et al 2017] [Kumar et al 2023] [Kurosaka 1984] [Lee et al 2023] [Lee et al 2019] [Lengyel-Kampmann et al 2024] [Lewis and Moore 1976] [Li and Wells 1999] [Li and Wu 2024] [Li et al 2022] [Liang and Yeuan 1997] [Lim and Chjng 1989] [Liu et al 2025] [Liu et al 2025] [Long et al 2026] [Longxin 2025] [Lu et al 2018] [Lu et al 2019] [Luo et al 2020] [Lück et al 2026] [Ma et al 2016] [Ma et al 2017] [Ma et al 2024] [Mackintosh and Dawson 1979] [Magrini et al 2023] [Massardo and Satta 1987] [Mayda et al 2024] [McCormick and Surko 1989] [Mechanisms of transonic blade-vortex interaction noise 1976] [Medd et al 2003] [Meng et al 2015] [Merchant 1949] [Merchant et al 2004] [Meyer et al 2024] [Michaud et al 2016] [Mirza-Baig and Saravanamuttoo 1991] [Moore and Reid 1972] [Moore et al 1978] [Moumen Idres and Muhamad Adi Muqri Saiful Azmi 2022] [Musgrave and Plehn 1987] [Mütschard et al 2021] [Nagai et al 1996] [Nakod et al 2025] [Namba 2001] [Newman 1988] [Nie 2003] [Oh 1999] [Oh and Oh 2000] [Onaka et al 2018] [Osborn and Steinke 1974] [Osborn et al 1973] [Palmer and Waterman 1994] [Pardowitz et al 2015] [Park et al 2024] [Paroubek and Kynčl 1998] [Pasupula and Mistry 2023] [Pavarani and Savage 1989] [Pelton 1976] [Pelton and Hannah 1976] [Peng et al 2024] [Performance Comparison of Counter Rotating Axial Fan and Single 2021] [Peters and Fottner 2002] [Pham et al 2020] [Place et al 1995] [Prahst et al 2015] [Pundhir and Sharma 1992] [Pérez et al 2024] [Qinghuan and Zhiqin 1988] [Rabe et al 1991] [Radermacher et al 2025] [Rajendran and Pachidis 2020] [Ran 2025] [Reemsnyder and Sagerser 1979] [Reemsnyder and Sagerser 1979] [Ren et al 2024] [Robles Vega et al 2023] [Rosell and Grönstedt 2026] [Rossikhin et al 2018] [Ryals et al 2026] [Ryan et al 1977] [Saathoff and Stark 1999] [Sagawa and Ono 2018] [Sagerser et al 1976] [Sanger 1994] [Sayari and Bölcs 1995] [Schaub and Krishnappa 1977] [Scheibel et al 2024] [Schmid et al 2019] [Schreiber et al 2017] [Shao et al 2023] [Sharma et al 1987] [Sharma et al 1991] [Shi and Yu 2023] [Shivaramaiah and Varpe 2023] [Stone 1958] [Streets 1960] [Streets 1963] [Stricklin and Hess 1969] [Suder et al 1987] [Sun et al 2017] [Sun et al 2021] [Suzuki and Kuno 1995] [Swan 1961] [Takamatu and Takezako 1967] [Tariq et al 2019] [Tesch and Pase 1983] [Tesch 1971] [THE CENTRIFUGAL COMPRESSOR STAGE 1964] [Tiwari et al 2024] [Touyeras and Villain 2004] [Trost and Schnell 2025] [Turner et al 2015] [Urasek and Moore 1972] [Van Zante et al 2002] [von Backstroem et al 2000] [Walitt et al 1997] [Wang et al 2017] [Wang et al 2021] [Wang et al 2024] [Ware et al 1974] [Wei and Kun 2015] [Wells et al 1989] [Wennerstrom 1984] [Wennerstrom 1987] [Wichert 1961] [Wolter et al 2017] [Wolters et al 2016] [Wright and Jones 1970] [Wright et al 1973] [Wyss et al 1993] [Xu et al 2023] [Xu et al 2026] [Yangang et al 2015] [Yin et al 2001] [Yu et al 2002] [Yu-bing et al 1981] [Zangeneh et al 2004] [Zeng and Guedes Soares 2025] [Zhang and Engeda 2018] [Zhang et al 2015] [Zhang et al 2020] [Zhang et al 2021] [Zhang et al 2024] [Zhang et al 2025] [Zhao et al 2015] [Zhou et al 2018] [Zhou et al 2022]
Clutches, gears and drivetrains
Clutches, gears, gearboxes, drive shafts and the transients of mechanical power transmission. Of these records, 79 were published in 2001 or earlier, and 111 in 2015 or later.
202 records. [Abdullah and Schlattmann 2016] [Advances in Aircraft Gear System Technology 1992] [Alavilli and Kadhar Maideen 2021] [Ali and Asiri 2022] [Ali et al 2017] [Amri et al 2016] [Aphale et al 2004] [Bao et al 2020] [Bao et al 2021] [Baz and Chen 1993] [Bemporad et al 2001] [Bemporad et al 2001] [Berthold et al 2017] [Bian et al 2025] [Biczó et al 2020] [Binney et al 2003] [Bugliari Armenio et al 2024] [Bunda et al 1972] [Burgan 1984] [Burroughs 1965] [Buyukataman and Kazerounian 1998] [Cacciola and Calabria 2026] [Candee 1943] [Cenbo et al 2015] [Chaloff et al 1974] [Chamehsara and Karami 2020] [Chavez et al 2017] [Chen 1998] [Chen and Bossler 1995] [Chen and Liao 2018] [Cheng et al 2018] [Chung et al 1997] [Cole 2025] [Corliss and Sprysl 1999] [Cowell 1947] [Dai et al 2026] [Darmstadt and Robuck 2018] [Dean 1979] [Design and Theoretical Analysis of Single Plate Clutch by Varying Friction Lining Materials 2015] [DeSmidt et al 2018] [DeSmidt et al 2013] [DeVita and Quenneville 1994] [Dewispelare and Stager 1981] [Drago 1985] [Drago and Mack 1987] [Du et al 2025] [Dub et al 2016] [Dundore and Schneider 1968] [Egawa 1956] [Faidh-Allah 2018] [Fan et al 2015] [Feng and Song 2017] [Feng et al 1999] [Feng et al 2001] [Feng et al 2003] [Feng et al 2003] [Feng et al 2003] [Firoozian et al 1991] [Friction contact in clutch assemblies 1987] [Gagnon et al 1997] [Ganesh et al 2021] [Gao and Barber 2002] [Gao et al 2001] [Gardner and Adams 1975] [Gargiulo 1986] [Gatta et al 2018] [Gibson and Taccini 1989] [Gil et al 1994] [Glielmo and Vasca 2000] [Gosselin et al 1998] [Handschuh 1992] [Handschuh and Bibel 1999] [Haria et al 2018] [He and Liu 2023] [He-yun et al 2021] [Holgerson 1997] [Holgerson 1999] [Holgerson 2000] [Holgerson and Lundberg 1999] [Hongo and Tanaka 1973] [Houjoh et al 2015] [Howe and McKibbin 1989] [Hozumi and Aihara 2018] [Hu et al 2016] [Huang et al 2025] [Huang et al 2025] [Iqbal et al 2015] [Ishutinov et al 2024] [Iwatsubo et al 1984] [Jabbar et al 2021] [Jabbar et al 2023] [Jang 2015] [Jang 2022] [Jin et al 2020] [Jones 1960] [Kabra 2022] [Kadhim et al 2020] [Kanemitsu 1985] [Kataria 2022] [Korzun 1976] [Krishna and Vancoillie 1999] [Kurushin et al 2018] [Leal Junior et al 2016] [Lee et al 2003] [Li and Yu 2001] [Li et al 2002] [Liao et al 2025] [Libraschi et al 2023] [Lin et al 2018] [Liu et al 2017] [Liu et al 2023] [Luo et al 2018] [Luo et al 2026] [Sudhan and Vasanthan 2021] [Ma et al 2016] [Mack 1965] [Mahmud et al 2018] [Mansouri et al 2000] [Mark 1987] [Martinsson and Liu 2016] [Mattiazzo et al 2002] [McCune 1993] [Miao et al 2015] [Mohire et al 2018] [Mohire et al 2019] [Multimode Clutch 2018] [Muscarello et al 2017] [Nagaya et al 1982] [Natsumeda and Miyoshi 1994] [Newcomb and Merritt 1962] [O’Brien 1945] [Oravský 1999] [Orzelowski and Wicher 2000] [Overfield and Crawford 1967] [Padmanabhan et al 2023] [Park and Choi 2020] [Penta et al 2017] [Pisaturo and Senatore 2018] [Pisaturo et al 2015] [Pisaturo et al 2016] [Pisaturo et al 2017] [Prosek and Barber 1958] [Qu et al 2016] [Radil and Berkebile 2020] [Reddy et al 1969] [Renfroe and Iverson 1986] [Research on Engagement Curve of Clutch Based on Optimization Theory 2018] [Rigbi 1997] [Rohan Ramesh et al 2021] [Routson et al 1992] [Sabri et al 2021] [Sakamoto and Aihara 2018] [Sato et al 2015] [Scheidler 2018] [Shaft-driven motor couplings 1995] [Sheng et al 2025] [Sherza 2019] [Sherza et al 2018] [Sherza et al 2022] [Sherzaa et al 2022] [Shin and Choi 2024] [Singh 1974] [Singh et al 2024] [Sivaramakrishnan 1981] [SoltanRezaee et al 2021] [Song et al 2026] [Szadkowski and McNerney 1992] [Szadkowski and Morford 1992] [Tan et al 2023] [Tatar and Schwingshackl 2018] [Terauchi et al 1981] [The model of friction for dry clutch working process simulation 2020] [Topczewska et al 2020] [Tsai and Roth 2001] [Tutulan et al 2004] [Umeyama et al 1998] [Uppaluri and Douglass 1991] [Vaidyanathan et al 1994] [Vigano et al 2024] [Voracek 1990] [Voskuijl et al 2018] [Vyrabov 1991] [Wang and Zhu 2020] [Wang and Zhu 2021] [Wei et al 2025] [Wei et al 2025] [Winter and Paul 1985] [Wu 1973] [Xiang et al 2023] [Xiaozeng et al 2015] [Xie et al 2016] [Xie et al 2021] [Yang et al 1998] [Yang et al 2026] [Zagrodzki and Truncone 2003] [Zhang and Yao 2019] [Zhang et al 2017] [Zhang et al 2021] [Zhu et al 2020] [Zhu et al 2023] [Zhu et al 2026] [Zimmer et al 2015]
Inlets, intakes and diffusers
Inlets, intakes and diffusers, including supersonic, diverterless and boundary-layer-ingesting inlets and inlet distortion. Of these records, 106 were published in 2001 or earlier, and 178 in 2015 or later.
291 records. [Abedi et al 2020] [Ahuja and Mavris 2020] [Alendar et al 2022] [Analysis of Flow Field Distortion in Ship Inlet System and Its Effect on Compressor Performance 2024] [Anderson 1984] [Anderson and Gibb 1996] [Antl 1970] [Arias et al 2023] [Askari and Abedi 2026] [Askari and Soltani 2017] [Askari and Soltani 2019] [Askari and Soltani 2020] [Askari and Soltani 2023] [Athanasakos et al 2020] [Azevedo et al 1990] [Babcock and Mani 2015] [Babcock et al 2019] [Bai et al 2025] [Bakhle et al 2018] [Ball and Ross 1971] [Bangert et al 1982] [Barr et al 2018] [Barr et al 2020] [Barry 1971] [Battiston et al 2025] [Baydar et al 2018] [Beach et al 2024] [Bedke and Gorrell 2021] [Benson and Anderson 1983] [Bevilaqua 2023] [Bhunia et al 2026] [Blumenthal et al 2018] [Bogar et al 1985] [Boles et al 2021] [Bond and Key 2025] [Bozeman 2023] [Bozeman 2024] [Braun and Podleski 2019] [Bravo Mosquera et al 2019] [Breugelmans 1975] [Burris 1966] [Burstadt et al 1971] [Calogeras 1969] [Campbell and Ellis 1970] [Campbell and Syberg 1984] [Campbell et al 1985] [Cao et al 2020] [Car et al 2000] [Carrier et al 2001] [Chandler and Montes 2019] [Chang and Hsu 1960] [Chen and Tan 2019] [Chen et al 2025] [Chennuru et al 2025] [Choe and Kim 2016] [Choe et al 2020] [Chun and Swanson 1964] [Cinquegrana and Vitagliano 2021] [Clark 1974] [Clauser 1954] [Collins 1970] [Colpin 1979] [Crosthwait 1970] [Cusator et al 2024] [Da et al 2020] [Daliri et al 2018] [Das and Trippi 1989] [Davis and Park 2017] [DeBardelaben and Sreenivas 2022] [Della Corte et al 2021] [Denner et al 1998] [Dickman and Takahashi 2016] [Domel 2015] [Effect of inlet Mach number on performance and flow structure of an axial supersonic through-flow fan cascade 2023] [El-Salamony and Teperin 2020] [Fan et al 2024] [Fan et al 2024] [Fan et al 2026] [Farr 1973] [Flores et al 1989] [Flow Field Analysis of Different Intake Bump (Compression Surface) Configurations on a Supersonic Aircraft 2017] [Fraiser 1960] [Frascella et al 2016] [Frohnapfel and O’Brien 2015] [Gaiddon and Knight 2003] [Giesecke and Friedrichs 2019] [Giri and Turner 2024] [Giri et al 2020] [Giri et al 2020] [Gray et al 2018] [Gray et al 2020] [Gray et al 2017] [Gray et al 2018] [Guan and Yarng 1987] [Guimarães et al 2018] [Guo et al 2015] [Haas and Karanian 1980] [Hagseth 1987] [Hah et al 2015] [Hall and Lieu 2021] [Hall et al 2016] [Hall et al 2017] [Hall et al 2022] [Halwas and Aggarwal 2019] [Harloff and Smith 1996] [Hawkins 1974] [Hawkins 1980] [He et al 2024] [Heinlein et al 2020] [Heinlein et al 2024] [Hirt et al 2017] [Howerton and Slater 2021] [Hunter and Cawthon 1984] [Hunter and Cawthon 1985] [Imfeld 1974] [Felder et al 2022] [Jin et al 2023] [Kamal and Livesey 1979] [Katoh et al 1998] [Kaya 1998] [Khaleghi and Jalaly 2016] [Khobragade et al 2021] [Kim and Choi 2024] [Kim and Kwon 2015] [Koncsek 1981] [Kramer and Hall 2025] [Krivec et al 1984] [Kucuk 2017] [Kumar et al 2018] [Kumar et al 2020] [Lamprakis et al 2025] [Lee and Boedicker 1985] [Lee et al 2018] [Lengyel-Kampmann et al 2024] [Li et al 2023] [Li et al 2024] [Li et al 2024] [Li et al 2025] [Lima et al 2019] [Liu and Vo 2024] [Liu et al 2023] [Liu et al 2023] [Liu et al 2025] [Lobo et al 2016] [Lu and Jain 1998] [Lv et al 2016] [López de Vega et al 2019] [López de Vega et al 2021] [Ma et al 2018] [Maekawa et al 1978] [Magrini and Benini 2026] [Malan and Brown 1994] [Mandal et al 2020] [Marien et al 2018] [Martínez Fernández and Smith 2020] [Marvin 1968] [Matesanz-García et al 2022] [Matwey et al 1983] [Mayer and Paynter 1994] [Mays 1969] [McCallum 1989] [McVey et al 1969] [Megat et al 2026] [Menegozzo and Benini 2020] [Menegozzo and Benini 2020] [Mennicken et al 2019] [Min et al 2018] [Moin and Lele 1998] [Moirou and Sanders 2026] [Moirou et al 2023] [Moore 1986] [Motycka 1985] [Mount 1964] [Mouton 2021] [Mufti et al 2019] [Muller and Gasko 1967] [Nagler 2026] [Nakamura 1988] [Numbers and Hamed 2003] [Obikane 1984] [Obrien and Cramer 1986] [Opalski and Sajben 2002] [Orme et al 2020] [Overall 1976] [Palko 1975] [Pandya and Uranga 2013] [Park et al 2026] [Paynter 1994] [Paynter and Chen 1983] [Paynter et al 1993] [Phan and He 2020] [Potonides and Mebes 1984] [Power and Prufert 1996] [Pyszka et al 2023] [Qiang et al 2024] [Qiu et al 2023] [Qiu et al 2023] [Qiu et al 2024] [Reedy and Gorrell 2025] [Rein and Koch 2015] [Rejeske and Stava 1974] [Rembaut et al 2023] [Reyhner and Hickcox 1972] [Reyhner and Hickcox 1972] [Rizzetta 1991] [Rodriguez 2004] [Sabo and Drela 2015] [Safarik and Polak 1996] [Saheby et al 2016] [Saheby et al 2016] [Sajben 2002] [Sajben 2004] [Sajben and Said 2001] [Saleem Yusoof et al 2016] [Samuelsson and Grönstedt 2021] [Sanders and Laskaridis 2020] [Sasson et al 2015] [Saunders and Keith 1991] [Secchi et al 2019] [Secchi et al 2021] [Sedlock 1985] [Seidel and Matwey 1983] [Seidel et al 1980] [Semmes and Weyer 1990] [Serrano et al 2021] [Shang et al 2021] [Shucheng and Xijun 1994] [Shur et al 2018] [Si et al 2016] [Siddharth et al 2026] [Sinha 1988] [Slater 2001] [Slater 2019] [Smith 1983] [Soltani and Askari 2018] [Sorensen and Bencze 1973] [Sorensen and Latham 1975] [Sorensen and Smeltzer 1972] [Sorensen et al 1973] [Stephens et al 2019] [Stubbs 1956] [Stuermer et al 2022] [Sudasinghe et al 2022] [Sun et al 2016] [Sun et al 2025] [Surber 1975] [Surber and Robinson 1983] [Surber and Sedlock 1978] [Sweep Optimization to Reduce Aerodynamic Loss in a Transonic Axial Compressor with Upstream Boundary Layer Ingestion 2024] [Syberg et al 1980] [T-4 inlet/engine compatibility flight test results 1989] [Tabanli and Yuceil 2021] [Taylor 1968] [Tekaslan et al 2021] [The verification of inlet/engine distortion compatibility 1988] [Tidow and Rudnik 2025] [Tindell 1973] [Tindell 1980] [Tindell 1987] [Tong and Yanagita 2019] [Trefny and Wasserbauer 1986] [Tudosie 2018] [Tudosie and Prisacariu 2022] [Uenishi et al 1992] [Uranga et al 2018] [Vadyak and Atta 1985] [Vadyak et al 1987] [Valencia et al 2015] [Vinz and Raichle 2024] [Vouros et al 2022] [Vu et al 2026] [Walter et al 2016] [Wang et al 2024] [Wegener 1977] [Werner et al 2022] [Williams and Hunt 1980] [Winkler and Davis 2017] [Woollett 1983] [Wu et al 2022] [Yang et al 2025] [Yao et al 2015] [Yu et al 2026] [Zhang and Vahdati 2018] [Zhang and Vahdati 2019] [Zhang et al 2015] [Zhang et al 2019] [Zhang et al 2020] [Zhipeng et al 2015] [Zhou et al 2019] [Zhou et al 2025] [Zimbelman and Rouser 2025]
Engines, thrust and installed performance
Engines and their thrust, installed performance, thrust lapse, cycles and propulsion control. Of these records, 108 were published in 2001 or earlier, and 40 in 2015 or later.
153 records. [Abbas and Riggins 2016] [Abercrombie 1979] [Akagi et al 1997] [Amundson and Holm 1989] [Andrianantara et al 2021] [Arnaiz 1975] [Avanzini and Matteis 1995] [Babcock and Mani 2017] [Baer-Riedhart 1982] [Bailey et al 1979] [Ball and Atkins Jr 1978] [Barrows 1980] [Beale 1986] [Bhatra and Mishra 2023] [Bird et al 1991] [Blevins and Wagner 2000] [Braman et al 1983] [Brandau 1965] [Brandt 2018] [Brown 1950] [Bruce and Rytting 1983] [Campbell 1974] [Cassetti 1978] [Cliff et al 1982] [Commander 1964] [Conners 1992] [Conners 1993] [Conners 1995] [Conners and Sims 1998] [Covert 1984] [DeCastro et al 2008] [Denning 1962] [Destarac and van der Vooren 2004] [Domel 2017] [Domel 2019] [Dugan 1972] [Dwinger and Friedrichs 2017] [Evans and Chamblee 1966] [Farokhi 1998] [Filinov and Ostapyuk 2019] [Flight-test evaluation of engine power effects on lift and drag 1985] [Fredrickson 1974] [Gissendanner 1981] [Goeing et al 2024] [Gogoi 2021] [Grunnet 1971] [Guajardo 2020] [Hashmi and Radhakrishna 2015] [Herrick 1986] [Hiers 2018] [Highly elastic carbon fiber reinforced plastic propulsion shaft 1996] [Hinz and Miller 1979] [Hou et al 2024] [Hunt and Gowadia 1981] [Jackson 1965] [Jakobsson 1951] [Kamman and Perryman 1982] [Keller 1982] [Kelley et al 1982] [Khalid 1989] [Khalid 1992] [Kim and Kim 2001] [Kim et al 2020] [Kitowski 1992] [Klann et al 1984] [Knox and Meyer 1984] [Kohl and Algranti 1957] [Korsun et al 2017] [Krasnow 1985] [Krouse et al 2022] [Kuenkler 1982] [Kuhn et al 1979] [Kurt 2024] [Kuzmin 2021] [Lake 1990] [Large 1981] [Leese 1966] [Liang et al 2024] [Lichtsinder et al 1998] [Lidor et al 2019] [Lieder et al 2025] [Liston and Small 1992] [Liu et al 2026] [Lockwood 1963] [Mace and Doane 1990] [Mace and Nyberg 1992] [Mandeles 1998] [Mattingly 1989] [Mihaloew and Roth 1982] [Moellmann and O’Connor 1967] [Moore and Collins 1937] [Muehter 1974] [Murphy and Lewis 1979] [Nebesar 1932] [Newell and Herrick 1979] [Papamoschou 1994] [Parker 1991] [Patnaik et al 2001] [Pinder et al 2001] [Pitt 1971] [Pizzo 1988] [Plourde et al 1983] [Powers and Robinson 1992] [Prince and McAulay 1950] [Pyle 1947] [Ray 1983] [Razinsky 1988] [Riggins 1996] [Rodgers 2001] [Rogers 2002] [Rosen 1972] [Saha and Jo 2026] [Salay and Elliott 1993] [Salay and Elliott 1996] [Samanich et al 1980] [Sanberg et al 1975] [Sasamoto 1921] [Schiewe et al 2019] [Schkolnik 1993] [Schmidt and Staudacher 2015] [Sears and Bajek 1958] [Shannak and Alhasan 2002] [Shovlin et al 1979] [Simpson 1986] [Smith and Wehofer 1982] [Sobel and Lallman 1988] [Su et al 2025] [Suder 2019] [Suh 1990] [Svoboda 2000] [Swavely and Soileau 1972] [Synylo et al 2020] [Takahashi 2022] [Takahashi 2026] [Tate and Gillard 1975] [Throndson 1982] [Toenskoetter 1984] [Trazzi 2004] [Universal Energy Systems Inc Dayton Oh 1995] [Vance 1973] [Vassilopoulos 1988] [Veres 2001] [Ward and Neeley 1959] [Wells and Urnes 1995] [Willis and Welliver 1976] [Winkler 2019] [Xie et al 2020] [Xu et al 2016] [Yiting et al 2021] [Yuksel and Aygün 2025] [Zhang et al 2015] [Zhang et al 2016] [Ziogas et al 2025]
Nozzles and thrust vectoring
Exhaust nozzles, thrust vectoring by mechanical and fluidic means, thrust reversers and deflectors. Of these records, 115 were published in 2001 or earlier, and 74 in 2015 or later.
197 records. [Acierno and Merzari 2022] [Adkins and Sherwood 1996] [Afridi et al 2023] [Afridi et al 2024] [Akatsuka 2026] [Anderson and Bradley 1987] [Aukerman 1991] [Aulehla and Besigk 1982] [Back et al 1972] [Banazadeh and Saghafi 2016] [Barnes et al 1984] [Berens 2019] [Bergman 1979] [Berrier 1983] [Berrier and Re 1978] [Bevilaqua and Lee 1980] [Bhabar and Mukesh Sharma 2025] [Bittrick 1984] [Blackman and Eigenmann 1981] [Bond et al 2001] [Boraas and Ashby 1969] [Bowers 1979] [Bowers and Buchan 1978] [Brodsky 1970] [Bronz 2019] [Burger 1983] [Burger 1986] [Burnes et al 2001] [Bursey and Dickinson 1990] [Calarese and Walterick 1978] [Capello et al 2019] [Capone 1975] [Capone 1979] [Capone and Reubush 1983] [Cheatham et al 1990] [Cheatham et al 1991] [Chen and Liao 2020] [Chouicha et al 2019] [Chouicha et al 2020] [Chu 1980] [Computational and Experimental Analysis of Optimized Dual Throat Fluidic Thrust Vectoring Nozzle Configurations 2024] [Crowe and Martin 2019] [Crown 1950] [Das et al 2025] [Davis and Hines 1976] [Davis and Spicer 1965] [Deere and Hunter 1999] [Deere et al 2007] [Domel 2015] [Domel 2017] [Dong et al 2025] [Dunn and Emery 1966] [Dutton 1987] [Eames and Mason 1988] [Eigenmann et al 1984] [Erwin et al 1964] [Esker and McArdle 1993] [Esker and Sedrick 1972] [Experimental Investigations on the Strut Controlled Thrust Vectoring of a Supersonic Nozzle 2020] [F119 Nozzle Flaps Tested 2005] [Ferlauto and Marsilio 2016] [Fernando et al 2026] [Finseth et al 1988] [Flamm 1998] [Flamm et al 2007] [Fujii et al 2020] [Gal-Or 1990] [Gill 1973] [Glezer et al 1985] [Goetz et al 1976] [Griffin et al 2000] [Ha et al 2025] [Hakim et al 2020] [Hamed et al 1997] [Hardy 1987] [Harris 1984] [Herrick 1988] [Herrick 1989] [Hienz and Vedova 1984] [Hiley and Bowers 1981] [Hoffman and Allman 1978] [Houx et al 2022] [Huang et al 2026] [Humphreys et al 1988] [Idzorek 1988] [Imlay 1986] [Islam and Islam 2017] [Islam et al 2018] [Islam et al 2018] [Jammalamadaka et al 2020] [Jimenez 2001] [Johnson 1990] [Jun et al 2018] [Jyothy and John Wessley 2023] [Kara and Kurtuluş 2024] [Kelley et al 2021] [Kentfield 1975] [Kim 2026] [King and Schnelker 1970] [King et al 1991] [Kumar et al 2021] [L’Ecuyer et al 1971] [Lecuyer 1970] [Li et al 2016] [Li et al 2020] [Liang 1989] [Lieu 1964] [Linderman et al 1974] [Liu et al 2025] [Liu et al 2026] [Lucas 1978] [Luo et al 2025] [Maiden and Petit 1975] [Malaek and Parastari 2001] [Matesanz et al 1995] [Mathur 1998] [McAmis and Bartlett 1991] [McArdle and Esker 1993] [McArdle and Smith 1990] [McLafferty and Peterson 1983] [Mehalic and Lottig 1987] [Mikhail 1979] [Miller and Protopapas 1985] [Moger and Ramsay 1964] [Nafi and Hasan 2019] [Naik and Chiarelli 1988] [Nayebi and Taeibi Rahni 2024] [Nocoń et al 2023] [Obye and Hakim 1984] [Orme et al 1998] [Orme and Sims 1998] [Ornob et al 2025] [Park et al 2025] [Pennington and Meintel 1980] [Peters 1985] [Presz and Greitzer 1988] [Pruitt and Bates 1992] [Rao 1958] [Ravindranath 2025] [Re and Carson 1991] [Resta et al 2022] [Romine and Johnson 1984] [Rosenberg and Esker 1980] [Ruetten 2018] [Sahu 1985] [Salahudden et al 2025] [Sarathe and Yadav 2018] [Schirmer and Capone 1989] [Schwagerus et al 2026] [Schwartz 1975] [Sedgwick 1975] [Seiner and Gilinsky 1995] [Sharjad et al 2022] [Shi et al 2024] [Shukla et al 2026] [Singh 2026] [Singh and Kushari 2008] [Sova 1988] [Speir and Blozy 1981] [Srivastava et al 2025] [Straight and Cullom 1982] [Strash et al 1997] [Strash et al 2000] [Surapaneni et al 2016] [Suresh et al 2026] [Suñol Jiménez et al 2015] [Taylor 1988] [Taylor et al 1973] [Thompson and Epstein 1977] [Thompson and Smith 1981] [THRUST VECTORING OF A SUPERSONIC RECTANGULAR NOZZLE BY USING DIFFERENT PLATE EXTENSIONS 2020] [Tsentis et al 2023] [Ulizar 1997] [Vohra and Kumar 2025] [Waithe and Deere 2003] [Wallace and Bowers 1982] [Wang and Peterson 1958] [Wang et al 2017] [Wang et al 2018] [Wilson et al 2003] [Wing and Asbury 1991] [Wing and Giuliano 1997] [Winkler 2015] [Winkler 2017] [Winkler 2022] [Winkler and Crowe 2019] [Wooten et al 1984] [Wu and Chow 1985] [Xu et al 2024] [Zafirov 2010] [Zebbiche and Youbi 2023] [Zhang et al 2024] [Zhang et al 2026] [Zhu et al 2016] [Zilz and Bailey 1985] [Zmijanovic] [Zukoski and Auerbach 1976]
Lift fans, ducted fans and the fan in the wing
Lift fans, ducted fans and fans in the wing or fuselage, the X-35’s own lift device and its relatives. Of these records, 88 were published in 2001 or earlier, and 118 in 2015 or later.
226 records. [Aaron et al 2003] [Aboelezz et al 2022] [Abrego et al 2002] [Acheson 2011] [Ai et al 2020] [Ai et al 2021] [Akturk and Camci 2022] [Ale Isaac Khoueini] [Ames 1975] [Atencio et al 1973] [Bai et al 2025] [Beeler 1965] [Beeler and Russell 1964] [Beeler and Volk 1965] [Bento et al 2020] [Benzakein and Kazin 1971] [Bevilaqua 1996] [Bevilaqua 1997] [Birckelbaw et al 1995] [Bland and Konsewicz 1976] [Bland et al 1976] [Brown et al 2019] [Cai et al 2019] [Cavage 1975] [Chakraborty et al 2022] [Chakraborty et al 2023] [Chen et al 2018] [Cheng and Pei 2020] [Cheng and Pei 2021] [Cheng and Pei 2022] [Cheng et al 2020] [Cho 2025] [Choi et al 2022] [Chung et al 1995] [Chung et al 1995] [Clark and Smith 1965] [Conceptual design of a 1973] [Cook and Hickey 1967] [Cook 1993] [Cousins et al 2026] [Curtiss 1965] [Davis and Ela 1969] [de Paula et al 2025] [Deng and Ren 2017] [Deng et al 2018] [Deng et al 2020] [Denisenko et al 2021] [Design definition study of 1975] [Diedrich 1971] [Diedrich 1975] [Diedrich et al 1972] [Dobek 1973] [Dorfling and Traub 2023] [Dos Santos et al 2024] [Doğru et al 2016] [Ducted fan] [Dugan et al 1971] [Ebus et al 2022] [Echavarria and Poroseva 2015] [Eldridge et al 1973] [Elliott 1976] [Engelbrecht et al 2022] [Envia 2016] [Esker and Roddiger 1979] [Fan et al 2017] [Far-field noise and internal modes from a ducted propeller at simulated aircraft takeoff conditions 1992] [Fasching and Kutney 1964] [Fazeli Asl and Moosapour 2017] [Fenwick 1966] [Ford 1973] [Franklin 1997] [Gao and Xu 2022] [General Electric Co Cincinnati Oh 1962] [General Electric Co Cincinnati Oh 1963] [General Electric Co Cincinnati Oh 1964] [Gerdes 1993] [Gerdes and Hynes 1975] [Gerdes 1993] [Gleiter 1976] [Gong et al 2021] [Gotlieb 1977] [Goudswaard et al 2024] [Grahame 1968] [Grahame 1969] [Guerrero et al 2003] [Guo and Zhou 2026] [Hall and Hodder 1971] [Hanjie et al 2023] [He et al 2013] [Heyson 1973] [Hicks et al 2023] [Hill and Waters 1974] [Hudson 1977] [Hudson and Gee 1977] [Hunt et al 1977] [Hwang et al 2023] [Jang et al 2012] [Jasudavisius 2021] [Jia et al 2025] [Jiang and Zhang 2016] [Jiang and Zhang 2016] [Jiang and Zhang 2017] [Jiang and Zhang 2018] [Jiang and Zhang 2021] [Jiang et al 2015] [Jiang et al 2023] [Jiang et al 2025] [Kang et al 2021] [Kantner et al] [Kim et al 2020] [Kirk et al 1972] [Knight et al 1973] [Kochanski 1966] [Kutney 1963] [Kutney 1964] [Lam 1998] [Lee et al 2016] [Li 2008] [Li and Liu 2023] [Li et al 2022] [Li et al 2024] [Li et al 2025] [Lieblein 1970] [Lieblein et al 1973] [Liu 2023] [Liu and Mi 2025] [Liu et al 2025] [Lowe and Sanger 1972] [Luo et al 2023] [Luo et al 2024] [Ma] [Maldonado and Fernandes 2024] [Maldonado et al 2024] [Manzoor et al 2020] [Martin 1964] [Meng et al 2026] [Mi 2020] [Miller and Papamoschou 2024] [Miller et al 2023] [Misiorowski et al 2019] [Miwa and Marubashi 2014] [MODELLING AND CONTROLLER DESIGN OF A NOVEL DUCTED FAN UNMANNED AIRCRAFT 2021] [Mumasha et al 2026] [Myers et al 2010] [Myers et al 2019] [Nardi et al 1999] [Novak 1975] [Obrien 1976] [Obrien 1976] [Odukoya and Jo 2026] [Palmer and Holdo̸ 2002] [Papamoschou 2023] [Park et al 2013] [Park et al 2015] [Park et al 2017] [Peddle et al 2009] [Peterson 1964] [Peterson 1965] [Prasad and Choi 2017] [Qing et al 2019] [Raeisi and Alighanbari 2017] [Renselaer 1977] [Ritschl et al 2003] [Cavage 1975] [Roelke and Zigan 1972] [Rolls et al 1976] [Ryu et al 2016] [Salazar et al 2020] [Sargent and Anemaat 2018] [Savage et al 2026] [Sayma et al 2003] [Schaub 1974] [Schlundt 1975] [Schmidt et al 2021] [Sellers et al 1977] [Sellers 1973] [Seo and Kim 2016] [Sheng and Sun 2015] [Sheng and Zhao 2016] [Sheng and Zhao 2017] [Sheng and Zhao 2022] [Sheng et al 2015] [Sheng et al 2015] [Shur et al 2016] [Simon 2024] [Simon et al 2023] [Smith 1966] [Sokhey et al 2002] [Sowers 1965] [Stewart 1979] [Stewart 1980] [Stockman et al 1973] [Stockman et al 1974] [Su et al 2025] [Su et al 2026] [Sullivan 1990] [Sun et al 2025] [Sun et al 2025] [Sylvester et al 2011] [Takeyeldein 2026] [Tauber et al 1976] [True 1967] [Truong and Papamoschou 2015] [Vanderlip and Schneider 1963] [Vasanthakumar et al 2019] [Wahl and Julian 1956] [Wang et al 2026] [Weinstein and Simmons 2024] [Wind tunnel and ground 1976] [Winfree 1998] [Xia et al 2020] [Xiang et al 2015] [Xiang et al 2016] [Xu et al 2016] [Young 2023] [Yu 2023] [Zabinsky et al 1975] [Zakaria et al 2019] [Zhang et al 2018] [Zhang et al 2021] [Zhang et al 2026] [Zhao et al 2022] [Zhao et al 2023] [Zhao et al 2025] [Zhao et al 2026] [Zhao et al 2026]
Fighter programmes, defence acquisition and cost
Fighter programmes, the Joint Strike Fighter and its international procurement, defence acquisition, cost and logistics. Of these records, 63 were published in 2001 or earlier, and 26 in 2015 or later.
109 records. [A Canadian Light Fighter 1940] [Analysis of the relationship between mass, speed and cost of an unmanned aircraft 2024] [Anderson 1989] [Armstrong and Levine 1988] [Ascani 1974] [Bangert et al 2017] [Behavior Patterns of Three Archetypal Arms Suppliers Based on Empirical Media Analysis of the First Korean Fighter Jet Program 2022] [Bell Aerospace Co Buffalo Ny 1955] [Boothe 1971] [Bye 1993] [Bykerk et al 2022] [Carlyle 1976] [Chace 2015] [Cheney 1988] [Cloos and Nelson 1990] [Coen and Foss 1985] [Cordeaux 1991] [Davis 1973] [Davis 2011] [de Haan et al 2023] [Defense Acquisition Univ Ft Belvoir Va 2004] [Dement 1990] [Donelson et al 1989] [Dudley 1986] [Eller 1994] [Enzinger 1988] [Fellers and Patierno 1970] [Figge and Bernhardt 1975] [Flight Test Programme 1970] [Franck and Dillard 2006] [Franck and Udis 2015] [Franck et al 2012] [Gideon and Wasek 2015] [Gran et al 1977] [Greer 2010] [Griffin 2012] [Guinivan 2004] [Hans et al 2021] [Harris and Lewis 2012] [Hayase 1974] [Herbst 1980] [Herbst and Ross 1970] [Hillaker 1983] [Hiyama 1974] [Horowitz et al 2016] [Jimenez et al 2016] [Jordan 1974] [Keeler 2005] [Kenyon 1974] [Kidd 1966] [Kitowski 1986] [Krahnstoever et al 2026] [Kwon and Sankar 1991] [Kwon and Sankar 1992] [Lewis 2002] [Lorell 1989] [Lyga 1990] [Lynch 1972] [Madelung 1977] [Malaek and Soltan-Mohammed 2001] [Martindale et al 1974] [McCown 2011] [McNicol 2014] [McNicol 2014] [McNicol and Wu 2014] [Meckstroth and Ordóñez 2020] [Meyn et al 1993] [Milligan et al 1994] [Milligan et al 1995] [Modeling and Data Fusion 2021] [Moore et al 2013] [Morra and Nicolosi 2025] [Nicholas et al 1984] [Nicholson 1985] [Parker 1986] [Parrish 1978] [Peteilh et al 2020] [Pikula 2000] [Rafiq and Qureshi 2022] [Raymer 1998] [Regnier and Nussbaum 2011] [Rice and Locksley 2000] [Rozum 1992] [Schwartz 1988] [Sepulveda and Smith 2019] [Sim 2025] [Simpson 2003] [Sobel 2013] [Spearman 1984] [St. Aubyn 2015] [Stanley 1980] [Stanniland 1974] [Stewart et al 2011] [Sun and Pang 2025] [Tamrat 1988] [Verma 2018] [Ward 1989] [Watkins 2019] [Weeks 1986] [Whitford 1995] [Wickert 1985] [Wildermuth et al 1974] [Wildermuth et al 1974] [Winbush and James O. 2012] [Woelk 1989] [Young et al 1995] [Zhang and Lin 2018] [Zhang et al 2021] [Zsolt 2018]
Weight, sizing and aircraft design
Weight and mass estimation, sizing and the conceptual and multidisciplinary design of aircraft. Of these records, 14 were published in 2001 or earlier, and 31 in 2015 or later.
46 records. [Ali and Al-Shamma 2026] [Basgall et al 2020] [Chai et al 1995] [Chakraborty and Mishra 2021] [Cleveland 1970] [COMPUTER-AIDED SYSTEM OF AIRCRAFT WEIGHT DESIGN 2018] [Crossley 2004] [Dababneh and Kipouros 2018] [Daidzic 2016] [Davies and Halliday 2024] [Dikbas and Atik 2018] [Goyal 2026] [Haibo and He 2022] [Hile and Denny 1954] [Horvath 2019] [Horvath and Wells 2018] [Hou et al 2021] [Hughes Tool Co Culver City Ca 1963] [Incorporating agility flight test metrics concurrently into the aircraft preliminary design process 1994] [INFORMATION MODEL OF AIRCRAFT WEIGHT PROFILE 2021] [Johnson 1972] [Kowalski et al 2021] [Liu et al 2023] [Mason 1990] [Morelli 2021] [Nigam et al 2015] [Olson and Henricks 2018] [Oole 1993] [Chiozzotto 2017] [Resulkulyeva and Serebryansky 2022] [Rodriguez and Liscouët-Hanke 2025] [Sabeti and Winter 2024] [Sabeti et al 2024] [Schrage and Patel 2019] [Solvey 1951] [Sreeletha et al 2019] [Sridharan and Govindarajan 2022] [Stamm and Woods 2024] [THEORETICAL FOUNDATION OF FORMATION OF AIRCRAFT WEIGHT APPEARANCE 2021] [Torenbeek 1972] [Valenti and Stanton 2024] [Ward 1983] [Whitford 1990] [Whitford 1994] [Wickman 1953] [Zhonghua and Haitao 2021]
Aircraft performance, takeoff, landing and ship operation
Aircraft performance, takeoff and landing, ski jumps and operation from ships, range and manoeuvre. Of these records, 47 were published in 2001 or earlier, and 18 in 2015 or later.
66 records. [Aircraft Ship Operations 1991] [Bai et al 2022] [Baker 1966] [Ball 1966] [Bardera-Mora et al 2019] [Bell and Pringle 1996] [Blinkhorn 1948] [Campbell 1960] [Chandrasekharan 1988] [Clark and Walters 1986] [Clark 1984] [Connelly 1982] [Dau et al 1965] [Digges 1971] [Ford 1998] [Frost 1968] [Frost and Rutherford 1963] [Green and Findlay 2016] [Horne and Leland 1962] [Jia et al 2024] [Kansas Univ Lawrence 1952] [Kansas Univ Lawrence 1952] [Kidwell 1963] [Kilner 1982] [Kim et al 2001] [Kolesar et al 2019] [Kuchinka 1966] [Kuznetsov et al 1985] [Laitone 1981] [Lee et al 1973] [Lehman 1964] [Li et al 2020] [Martinez Rodriguez and Blaesser 2024] [Mathur and Atkins 2025] [Micklos 1991] [Middleton and Srivatsan 1987] [Middleton et al 1988] [Middleton et al 1992] [Miller and Koch 1985] [Moore et al 1979] [Ouellette 2025] [Paulson et al 1988] [Philpot et al 1993] [Ramsey and Dixon 1967] [Rudowsky et al 2002] [Samuels 1992] [Sharpe and Hansman 2024] [Simpson 1972] [Simpson 1979] [Smith et al 1979] [Snyder 1950] [Srivatsan et al 1986] [Stepniewski 1940] [Suharev et al 2019] [Sóbester 2021] [Thakur and Kumar 2021] [Trobaugh and Obrimski 1980] [van Es 1999] [Vipin and Vijayakumar 2022] [Wittenberg 2001] [Yechout 1988] [Yokell and Baker 1994] [Yoo et al 2024] [Yue et al 2015] [Yue et al 2015] [Zhang et al 2025]
Kinematics of joints, mechanisms and manipulators
The kinematics of joints, spatial mechanisms, manipulators and constant-velocity couplings, the geometry of the swivel module. Of these records, 54 were published in 2001 or earlier, and 81 in 2015 or later.
142 records. [Antonov and Fomin 2024] [Antonov et al 2025] [Arrouk et al 2018] [Baigunchekov et al 2021] [Baron 2015] [Butler 1964] [Canfield et al 1994] [Chachada et al 2016] [Chang 2015] [Chernyshenko and Privalov 2004] [Chiaverini et al 1990] [Colbourne 1972] [Configuration Design and Workspace Analysis of Parallel Mechanism Driven by Eight Cables for On-orbit Assembly 2021] [Conti et al 1992] [Dasgupta 2002] [Day et al 1983] [Design and Kinematic Analysis of Automatic Articulated Robot 2022] [Dong et al 2022] [Dwarakanath et al 1992] [Erkaya et al 2016] [Erturk and Gomec 2020] [Essomba and Nguyen Vu 2018] [Faria et al 2018] [Federspiel 1979] [Freudenstein et al 1984] [Freudenstein et al 1994] [Ghaedrahmati and Gosselin 2022] [Graham and Bhandari 2022] [Gupta 1973] [Han et al 2002] [Han et al 2024] [Hansen 1965] [Hasegawa et al 1981] [Hayes and Caverly 2020] [He et al 2018] [Heiran et al 2017] [Hernández et al 2003] [Hertz and Hughes 1998] [Hoh et al 1981] [Ichikawa and Watanabe 1995] [Ichikawa and Watanabe 1996] [Innocenti 1999] [Jinxin et al 2026] [Kamada et al 2019] [Kara-Mohamed et al 2023] [Karamoozian et al 2018] [Kim and Park 2001] [Kinematic Analysis of RSSR spatial mechanism, A Review 2017] [Kong 2015] [Kong 2016] [Kong 2016] [Krishna et al 1994] [Lang et al 2024] [Lee and Yan 1992] [Li and Li 2024] [Li et al 2016] [Li et al 2016] [Li et al 2017] [Li et al 2020] [Li et al 2021] [Li et al 2026] [Liao et al 2024] [Liu and Zhao 2019] [Liu et al 2004] [Lu et al 2022] [Mahna and Asnani 1989] [Marter et al 2020] [Martins and Guenther 2003] [Meng and Lu 1993] [Mruthyunjaya and Raghavan 1984] [Nag et al 2017] [Nango and Shizu 2001] [Nango et al 2001] [Nery et al 2024] [Ni et al 2026] [Nibin et al 2024] [Norledge 1998] [Nouri Rahmat Abadi et al 2019] [Nurahmi and Gan 2018] [Osman and Segev 1972] [Osman et al 1991] [Otani 2023] [Ou and Tsai 1993] [Pennestrì 1992] [Petrescu and Petrescu 2019] [Piipponen et al 2015] [Pomrehn and Papalambros 1993] [Qi et al 2020] [Qiu and Xu 2021] [Rea et al 2022] [Righettini et al 2021] [Robson and Lee 2021] [Rosenberg and Křen 1987] [Rusli and Aveka 2021] [Sakhapov et al 2021] [Sandor et al 1984] [Schlundt 1976] [Sheikhpour and Bamdad 2017] [Shi et al 2023] [Shi et al 2026] [Shinoda et al 2016] [Shujun 1990] [Skvortsov 2016] [Soylu and Burak Akbulut 1997] [Tang et al 2021] [Tang et al 2026] [Tavkhelidze and Davitashvili 1974] [Tian et al 2018] [Tian et al 2025] [Urbinati and Pennestrì 1998] [Vahid Amirinezhad and Uyguroğlu 2015] [Wang and Gosselin 1996] [Wang et al 2014] [Wang et al 2022] [Watanabe et al 1993] [Watanabe et al 1998] [Watanabe et al 2001] [Wei et al 2019] [Wei-Liang and Qi-Xian 1989] [Wei-rong and Xing-yong 1989] [Wu et al 2021] [Wu et al 2023] [Xiangyang et al 2019] [Xiaolong et al 2018] [Xu et al 2018] [Yang and Yao 1992] [Yang et al 1992] [Yotov Daskalov 1990] [Yu et al 2018] [Yu et al 2018] [Yu et al 2021] [Yuan et al 2024] [Zhang and Wei 2015] [Zhang et al 2025] [Zheng et al 2023] [Zhou and Fenton 1992] [Zhou and Xi 1998] [Zhou et al 1995] [Zhu et al 2021] [Zlatanov et al 1992] [Zou et al 1996] [Özgören 1999]
The atmosphere, temperature and aerodynamic heating
The standard atmosphere, recovery temperature, the kinetic heating of aircraft structures and the temperatures met at supersonic speed. Of these records, 14 were published in 2001 or earlier, and 5 in 2015 or later.
20 records. [Asai 1994] [Asai 1995] [Divakar and Rajalakshmi Samaga 2022] [Feng 2016] [Gringorten 1967] [Gringorten and Tattelman 1970] [Guttman and Crutcher 1968] [Keçeci et al 2025] [Kitchenside 1958] [Krueger and Minzner 1976] [Luce 1949] [Mahlmeister et al 1955] [Murphy 1957] [Nangia 2011] [Nonweiler 1956] [Shiryaev and Serebryansky 2022] [Simsek et al 2016] [Stalder et al 1950] [Taylor 1968] [Walker 1955]
Fuels and fuel properties
Aviation fuels, their composition, properties and density, and the effect of alternative fuels on engines, aircraft and missions. Of these records, 5 were published in 2001 or earlier, and 18 in 2015 or later.
23 records. [Aircraft Research and Technology 1980] [Alquist et al 1953] [Behnke et al 2022] [Canteenwalla and Chishty 2017] [Comesana et al 2026] [Duong et al 2020] [Han et al 2026] [Iyer and Takahashi 2024] [Knoerzer et al 2018] [Kosir et al 2020] [Kurt 2026] [Liu et al 2022] [Naval Air Test Center Patuxent River Md 1957] [Oh et al 2024] [Oğur et al 2024] [Pires et al 2018] [Rijal et al 2025] [Friedman et al 1984] [Ruan et al 2019] [Russell and Mattes 1974] [Sasi et al 2023] [Vozka et al 2019] [Woehler et al 2023]
Aircraft, jet and rotor acoustics
The noise of hot supersonic and military jets, carrier decks, rotors and vertical-lift aircraft, its prediction and its measurement. Of these records, 7 were published in 2001 or earlier, and 14 in 2015 or later.
21 records. [Afsar et al 2019] [Aujogue et al 2022] [Berry and Harris 2024] [Berry and Speakman 1993] [Goparaju et al 2018] [Gryazev and Karabasov 2018] [Gryazev et al 2022] [Homans et al 1978] [Knott 1974] [Pascioni et al 2024] [Leib et al 2017] [Oetting 1974] [Plumblee 1967] [Powers et al 2015] [Powers et al 2018] [Prasad and Gaitonde 2021] [Speakman et al 1978] [Rizzi et al 2025] [Tam 2015] [Wall et al 2017] [Webster 1971]
Ejectors and thrust augmentation
Ejectors and thrust augmentation, the lift technology the shaft-driven fan displaced. Of these records, 78 were published in 2001 or earlier, and 6 in 2015 or later.
90 records. [Alperin and Wu 1983] [Alperin and Wu 1983] [Barankiewicz 1991] [Barankiewicz et al 1992] [Barankiewicz et al 1994] [Barankiewicz 1993] [Bernal and Sarohia 1983] [Bernal and Sarohia 1984] [Bevilacqua and Dejoode 1979] [Bevilaqua 1974] [Bevilaqua 1977] [Bevilaqua 1984] [Bevilaqua 1987] [Burley 1971] [Burt et al 2019] [Byrnes et al 1974] [Chen et al 2021] [Cheng et al 1973] [Clark 1995] [Corsiglia et al 1989] [Dailey 1955] [Dijkstra et al 1997] [Doonan and Kuchar 1992] [Drummond 1989] [Drummond and Barankiewicz 1990] [Dudley et al 1990] [Emanuel 1984] [Fabri and Le Grives 1960] [Fancher 1971] [Franke and Unnever 1985] [Garland 1987] [Gates and Cochran 1961] [Giles 1944] [Graham 1973] [Green and Cyrus 1977] [Gregory and Han 2003] [Hindson and Hardy 1980] [Huang et al 1999] [Hunter et al 2002] [Jones 1975] [Katz 1988] [Kim and Park 2025] [Kinzie et al 1998] [Knox 1962] [Krasheninnikov et al 1996] [Krothapalli et al 1985] [Kurtz 1976] [Landry 2005] [Lashkov and Shumilkina 1982] [Lissaman 1969] [Lopez et al 1979] [Luidens et al 1984] [Lund et al 1986] [McNeill et al 1995] [Minardi 1982] [Naumowicz and Smith 1992] [O’Keefe et al 1973] [Oganyan and Loginov 2025] [Papamoschou 1996] [Parkala and Kandath 2026] [Peterson et al 1995] [Poppen et al 1991] [Presz et al 1994] [Quinn 1973] [Quinn 1973] [Salter 1974] [Salter 1975] [Seiler and Schum 1978] [Seiler and Schum 1979] [Sharon 1975] [Shehadeh et al 2004] [Smith et al 1992] [Sotheran 1982] [Streiff and Henderson 1974] [Sully and Whittley 1987] [Tacina et al 2004] [Tamm and Spyropoulos 2018] [Throndson 1973] [Tillman and Presz 1993] [Uhuad and Franke 1993] [Viets 1977] [Weber 1960] [Weber 1960] [Weber 1961] [Whitfield and Blackburn 1965] [Whitley et al 1996] [Willis et al 1982] [Witte 1969] [Yang et al 1985] [Yungster 2003]
High-temperature and rotating seals
High-temperature, rotating, brush, finger, foil and labyrinth gas seals, the sealing problem of the swivel joint. Of these records, 6 were published in 2001 or earlier, and 5 in 2015 or later.
15 records. [Beermann et al 2015] [Cangioli et al 2018] [Dellacorte and Steinetz 1992] [El 1983] [Fellenstein et al 1996] [Gardner 1999] [Goff et al 2015] [Kerr and Bensmiller 2024] [More and Datta 2003] [Oswald et al 2004] [Proctor et al 2002] [Salehi and Heshmat 2000] [Su et al 2023] [Taylor et al 2004] [Wittig et al 1994]
Where the Framing Breaks Down
The Deflationary Reading Can Be Pushed Too Far
The argument above is capable of proving too much. If one insists that a demonstration teaching the engineers nothing new is theatre, then almost every public demonstration in aviation history is theatre, which is a sign the criterion is wrong rather than a discovery about aviation.
A demonstration has a second, legitimate function, to establish that separately verified capabilities compose. Engineers frequently find that they do not. Doing the three in sequence tests the aircraft’s ability to do them in sequence, including the fuel state, the thermal state, the pilot’s workload and the systems’ behaviour after a long, busy sortie. None of those is captured by the arithmetic in this article, and all of them are real.
Mach 1.05 Is the Worst Place on the Drag Curve, Not the Easiest
The claim that the supersonic leg was cheap should face its strongest counter-argument. Transonic drag rises steeply and peaks a little above Mach one, so Mach 1.05 is close to the most expensive point on the drag curve, far from a comfortable cruise. An aircraft that reaches Mach 1.05 in level flight has demonstrated that it can push through the peak, which is a stiffer test than reaching a higher Mach number would be once past it.
That counter-argument is correct on drag and does not disturb the thermal conclusion, which is separate and which the arithmetic settles. It also does not disturb the ordering conclusion. A conclusion that survives its own best counter-argument is worth more than one that needed the argument suppressed.
The Assumed Inputs and What They Carry
Several results here depend on quantities that were never published, and the conclusions that would move with those assumptions should be set out explicitly.
| Assumed quantity | Used for | Does the conclusion depend on it? |
|---|---|---|
| Fan polar moment of inertia, 25 to 50 kg·m² | Clutch energy magnitude | No. The halving identity is exact and the time constant is under a fifth of a second across the bracket |
| Stage loading coefficient of 0.40 | Estimating fan speed | Weakly. Every threshold in the counter-rotation table is an ordinary fan speed regardless |
| Roll-post arm, 2.5 to 4.0 m | Counter-rotation threshold | No. The conclusion is stated across the whole bracket |
| Zero-lift drag 0.025, rolling friction 0.03, nozzle aft until unstick | Ground roll | Slightly. The minimum of 307 to 422 feet stays short of 500 across the weight bracket |
| Rear nozzle at its published 18,000 lbf at eighty knots | The Mission X unstick coefficient | No. The finding is that the record cannot pin a coefficient, and a smaller nozzle thrust only raises the bound of 0.637 |
| Transonic drag coefficient 0.035 | Dash thrust margin | No. The margin is 2.389 and would survive a doubling |
| Sortie fuel burn of 3,500 lb | The floor of the takeoff-weight bracket and the landing weight margin | The gain figure, yes. The finding that the ordering helps does not, since the gain exceeds unity for any positive burn |
| Fan to nozzle separation of 7.5 m | Moment arms and the centre-of-gravity band | Only for the arms in metres. The station as a fraction, 0.4737, needs no separation at all |
| Thrust split authority of 10 percent | The pitching-moment threshold | Weakly. It sets the threshold height, and the finding is that the threshold is near a metre rather than far from it |
| Radius of gyration at 0.20 to 0.25 of span | Roll control power | No. The bracket is reported and the residual after a single-rotation reaction is derisory across all of it |
| Oswald efficiency of 0.75, zero-lift drag 0.018, wave drag 0.017 | The dash drag build-up | No. Induced drag is 0.0027 of a total 0.0377, so the build-up is insensitive to it |
| Thrust lapse exponent of 0.7 | Thrust available at altitude | No. The sensitivity is tabulated and the margin survives 0.6 to 1.0 |
| Clutch plate mass of 20 kg | The plate temperature rise | No. It scales the rise linearly and the conclusion is that the bound is absurd, not that the rise is a particular number |
| Clutch engagement time of 9 s | The power bound on clutch dissipation | No. The bound exceeds the dissipation for any engagement longer than about a third of a second |
A Demonstration Is Not Only an Experiment
The framing this series uses treats a research aircraft as an instrument for answering a question, and the X-35 does not fit that framing cleanly. It was a competitor as much as an instrument. Its purpose included persuading a customer, and a machine built partly to persuade is not well described by asking only what it measured. The framing does not break down so much as become incomplete, and Mission X sits in the space that it leaves.
The Source Base
Both Halves, Counted and Not Only Divided
The count and the fraction are reported together, because they move independently and reporting only the fraction misrepresents both. Adding contemporary sources leaves the period count untouched while lowering its share, and adding period sources does the same to the contemporary share. Neither movement is a fact about coverage.
The research survey holds 4,311 research records drawn from Crossref, the NASA Technical Reports Server and the Defense Technical Information Center. Of these, 2,052, or 47.6 percent, were published through 2001, the year the competition was decided, and 1,996, or 46.3 percent, were published from 2015 onward. Of the contemporary half, 965 records were published from 2022 onward. The median publication year of the 4,301 dated records is 2003.
The Period Vocabulary for This Article’s Derived Subjects
Several subjects this article’s equations name are filed in the period literature under other words. The mechanics beneath an equation are not the same literature as the technology above it. This article says momentum drag, and the period reports say inlet momentum drag, ram drag, lift engine installation losses and propulsion-induced effects. This article says canted joint, and the period says swivel duct, deflector, skewed axis coupling and spatial mechanism. The records cited under those subjects are filed under the period’s words, and the period writes installation effects in the plural, so a reader looking for them should search in the period’s vocabulary rather than the article’s.
A Designation With Almost No Literature of Its Own
This is the sharpest finding the source base contains.
Two research records this article cites carry “X-35” in their titles, and both are papers of 2002. They treat the X-35B’s flight control law design and flying qualities in Walker and Allen 2002 and the jet effects test effort in Buchholz 2002. A paper of the same year, Roberts 2002, names the rival’s X-32B. No later research title carries either designation.
The previous two articles found something that looked similar and means the opposite. The X-33’s cluster held sixty records, of which the X-33 article reports fifty-seven predate 2002. The X-34’s held its records and every one predated 2002. Both programmes were cancelled, and the conclusion drawn was that a cancelled programme stops generating literature under its own name, so the documentary trace of a vehicle measures how long it survived rather than what it contributed.
The X-35 is the control case for that claim and it fails it in an unexpected direction. This programme was not cancelled. It won, and its architecture went into production and is flying now. And its designation has a smaller documentary trace than either of the cancelled vehicles, because it barely had one.
What the literature carries instead is the programme name and the product name. Counted by title among the research records this article cites, 54 name the Joint Strike Fighter in full or as JSF, the dated ones running from 1996 to 2026. Nineteen name the F-35, the dated ones running from 2003 to 2019, and thirteen of those also name the Joint Strike Fighter. Beyond those two papers of 2002, nothing names the aeroplane.
The inference this supports is narrower than it first appears, and it is worth stating carefully. The X-35 designation was applied to competition demonstrators built by a contractor and flown for a source selection, and that is not the institutional arrangement that produces published reports. The X-33 and the X-34 were agency programmes with agency reporting obligations, which is why their cancelled programmes still left a paper trail. So the finding is about who was writing rather than about who won, and the three cases together say that the documentary trace measures the institution rather than the aircraft.
The Reference Works
The following books and monographs were drawn on for the standing theory rather than for the aircraft, covering propulsion, powered lift, rotor and fan aerodynamics, aircraft performance and flight test method. Almost none of them is about the X-35 and that is the point, since the relations this article displays are older than the aeroplane and better documented than it.
- The gas turbine
- Aircraft engine design
- Aircraft Engine Design
- Jet propulsion turbojets
- Gas turbines and jet propulsion
- Gas turbine theory
- Aircraft propulsion
- Chemistry problems in jet propulsion
- Jet propulsion engines
- Vertical takeoff and landing aircraft
- V/STOL aircraft
- Flying qualities of piloted V/STOL aircraft
- Fighter Aircraft Design
- Technical Evaluation Report on the Multi-Panel Symposium on…
- The feasibility of the jet-flap rotor as a lift generator for…
- Fighter aircraft design
- Gas Turbine Theory
- 186 kW lightweight diesel aircraft engine design study
- Helicopter theory
- V/STOL aircraft development
- Flight Testing the Fixed Wing Configuration of the Rotor…
- Flight testing the fixed-wing configuration of the rotor…
- Future of V/STOL aircraft systems
- Aircraft engine design
- Special course on fundamentals of fighter aircraft design
- Computer simulation of a pilot in V/STOL aircraft control…
- Aircraft Design
- Harrier Jump Jet
- Active control of V/Stol aircraft
- Basic helicopter aerodynamics
- Lockheed Skunk Works
- Lockheed’s Skunk Works
- Lockheed’s Skunk Works - The First Fifty Years
- Skunk Works
- Lockheed Martin’s Skunk Works
- Elements of gas turbine propulsion
- Gas turbine theory
- Jet propulsion
- Joint strike fighter
- Aircraft Performance And Design
- Principles of Helicopter Aerodynamics
- Basic helicopter aerodynamics
- Gas turbine theory
- Lockheed Martin Skunk Works
- Principles of Helicopter Aerodynamics Cambridge Aerospace…
- American X-vehicles
- Flight Testing of Fixed-Wing Aircraft Aiaa Education Series
- Jet Propulsion
- Lockheed Martin F-35 Joint Strike Fighter
- Harrier Jump Jet
- The AV-8B Harrier Jump Jet Edge Books
- V/STOL Aircraft Design
- Gas Turbine Theory
- Lockheed F-35 Joint Strike Fighter
- AV-8B Harrier Jump Jets Torque Military Machines
- AV-8B Harrier jump jets
- Aircraft Propulsion and Gas Turbine Engines
- Aircraft propulsion
- F-35 Lightning II
- Harrier Jump Jet – A history
- Aircraft Propulsion
- Aircraft design
- American X-Vehicles
- F-35 Lightning II
- American X-Vehicles An Inventory - X-1 to X-50
- Luftwaffe X-Planes
- Aircraft Propulsion
- Commercial Aircraft Propulsion and Energy Systems Research
- Harrier
- Aircraft Propulsion and Gas Turbine Engines, Second Edition
- Joint Strike Fighter
- F-35 Lightning II
- Joint Strike Fighter
- Aircraft Performance and Design
- 75 Years of the Lockheed Martin Skunk Works
- Aerothermodynamics and Jet Propulsion
- Electrified Aircraft Propulsion
- F-35 Lightning II
- Run Time Assurance for Electric Vertical Takeoff and Landing…
- Fundamentals of Jet Propulsion with Power Generation…
- F-35 Lightning II
What the Record Does Not Contain
There is no published flight test report for the X-35B, and the standard survey of the American X-vehicles treats the type in a page. The two papers of 2002 named above are the only research records whose titles name the aircraft. There is no published weight statement, no published engine deck, no published fan map, and no published moment of inertia for the lift fan. The quantitative reconstruction in this article is built entirely from performance figures released for publicity and from the physics that connects them, and the article says so at every point where an assumption was needed.
The Definition of Primary
Primary for this subject means the reports and papers written during the competition and the technology work that preceded it, together with the contemporary programme announcements that record what was flown and when. The flight chronology in this article rests on the latter, because the demonstrator campaign was a contractor activity and its detailed test reports are not public.
For counting, primacy is read from the identifier. A record is a report primary when its address is on the NASA Technical Reports Server or it carries a digital object identifier under the 10.21236 prefix, which Crossref registers for Defense Technical Information Center reports. By that rule 651 of the 4,311 research records, or 15.1 percent, are report primaries. The rule does not reach the conference papers of the competition period, such as the inventor’s own papers and the two papers of 2002 on the X-35B, so 15.1 percent is a lower bound on how much of the survey is first-hand.
Thin Subjects
Seven subjects are thin in the cited literature, and they are not all thin for the same reason. A subject can be thin because the work was never done, because the heading is wrong, or because the knowledge is so settled that it stopped generating papers, a distinction the X-34 article draws.
The counts are taken over the research records this article cites, so that anyone can repeat them. A record counts for a subject when its title contains one of the phrases in the second column, matched without regard to case and with a hyphen read as a space, and a record is modern when it was published in 2015 or later. A phrase count also catches a title that uses the phrase in another sense, such as an installed thrust reverser under the thrust lapse phrases, and it misses work filed under another heading, which is what the last column records.
| Subject | Title phrases counted | Records | Which kind of thin |
|---|---|---|---|
| Ground roll and takeoff distance | ground roll, takeoff distance, take-off distance, rolling friction | 1, none modern | Settled. A closed-form result in every performance textbook, and this article derives it in two lines |
| Disc loading | disc loading, disk loading | 10, one modern | Settled. Nine of the ten date from 1948 to 1971, when disc loading was the parameter by which VTOL concepts were compared, and the subject now sits inside momentum theory and lift fan work |
| Jet footprint and ground erosion | ground erosion, surface erosion, deck heating, jet footprint, impingement pressure | 3, one modern | Wrong heading. It lives inside impingement and ground environment work, in the cluster on jet impingement, ground effect and hot gas ingestion |
| Rotor spin-up and inertia | spin-up, spin up, spinup, rotational inertia, polar moment, flywheel | 0, none modern | Wrong heading. It lives inside drive system transient work |
| Thrust lapse with altitude | thrust lapse, installed thrust, altitude performance | 8, one modern | Wrong heading. It lives inside installed performance and engine decks |
| Stagnation temperature and kinetic heating | stagnation temperature, recovery temperature, kinetic heating, aerodynamic heating | 8, two modern | Moved. The six older records date from 1949 to 1968 and treat the kinetic heating of aircraft structures, and by title the two modern ones are heating prediction tools for high-speed and supersonic vehicle design rather than studies of the transonic case |
| Standard atmosphere | standard atmosphere, atmospheric model, hydrostatic | 2, one modern | Settled. Only one of the two records was published in 2015 or later |
One homonym is worth naming because it falls on the article’s own term of art. Figure of merit is a standard quantity in thermoelectrics, where it is written as a dimensionless number, and in plasmonic and photonic sensing. In the contemporary literature, hover efficiency and figure of merit also name properties of solar cells and graphene sensors, and the thermoelectric and photonic records are excluded from this survey.
None of these is padded and none is reported as a gap in the field. Four of the seven are headings rather than subjects, and the article cites the literature where it actually lives. The three that are genuinely settled rather than misheaded are the ground roll, disc loading and the standard atmosphere, and across the three the article cites two records under their phrases published in 2015 or later.
What the Survey Admits
A record is admitted only when a person reading its title finds it on this article’s subject. Much of this subject’s vocabulary also names something else, and a record that shares only such a word is excluded. Acquisition also names corporate mergers, biomedical signal recording and seismic surveying. Figure of merit also names a quantity in thermoelectrics, photonics and power electronics. Ski jump also names dam spillways and a sport, downwash also names chimney and building plumes, and outwash also names glacial outwash plains. Engine performance at altitude also names diesel and gasoline engines for road vehicles, and erosion also names the erosion and corrosion of metals by liquid and slurry jets. Hot gas ingestion also names the ingress of hot gas through a turbine rim seal, which is a different flow from the reingestion of a lift jet’s exhaust. Harrier also names a bird, swivel also names furniture, textiles and a dictionary headword, and electric propulsion also names the ion, Hall and plasma thrusters of spacecraft. Impinging jets of water, liquid fuel, sprays and quenching flows share a word with the jet footprint and none of its subject. Correction, erratum, retraction and withdrawal notices, figure, table and supplementary-material records, peer-review reports, conference programmes, news items and journal front matter are excluded as well, because a survey counts research works and those are parts of works or editorial events rather than works. Reviews of books, unsigned reference entries, reference entries of two pages or fewer, and the abstracts of papers, patents and reports reprinted in the abstract sections of other journals are excluded on the same ground, while a signed encyclopedia article and a textbook chapter are research works and stay.
Some records of doubtful relevance are kept. Underwater vehicle and marine vessel thrust allocation, planetary gearboxes, counter-rotating pumps and turbines, the kinematics of spatial mechanisms and manipulators, gas jets impinging on plates and automotive clutches each share the control-allocation, kinematic, ground-environment or drivetrain problem this article treats. The clutch records are kept in particular because the drivetrain literature that owns the clutch is largely automotive, but only where they treat the engagement, its energy or its heat. Electrical machines, batteries and power electronics written for electric aircraft are excluded, because their subject is the machine rather than the aircraft, while aircraft-level studies of battery and powertrain sizing are kept. A reader may weigh the doubtful classes accordingly.
A record whose only link to this subject is general aeronautics is excluded, and so is one about a vehicle class the argument never uses. Hypersonic and combined-cycle propulsion, rockets, launch vehicles and spacecraft, rotor dynamics and helicopter airworthiness, aircraft systems, maintenance, health monitoring and instrumentation, airline and airport operations, the noise of transport engines and airframes, transport, supersonic-transport and high-lift aerodynamics, boundary-layer physics, combustion and emissions, hydrogen storage, railway and road-vehicle aerodynamics, road-vehicle torque allocation, automotive and marine transmissions, torque converters and shift control, gear manufacturing and gearbox noise, engine accessories, jet impingement in cooling systems and heat exchangers, flapping-wing and lighter-than-air craft, and design studies of unrelated configurations therefore fall outside the survey, as do bibliographies and proceedings volumes. A signed comment on a paper, a discussion of it and its author’s closure or reply are research works, because each argues about a result, and are admitted when their subject is, while an unsigned item of these kinds and a referee’s report are not. A record on a method or a phenomenon the argument relies on is kept whatever vehicle it concerns, which is why rocket plumes on soil, ejectors of any working fluid and boundary layer ingestion on transport aircraft remain.
Every research title has been read for relevance, so the off-topic share that remains is a matter of reading judgement. A reading of titles cannot show that a work is relevant in substance, so this is a statement about titles only.
Epistemic State
Historical Fact
The X-35A first flew on 24 October 2000 and completed its conventional campaign on 22 November 2000. The X-35C first flew on 16 December 2000 and completed 73 flights and 58 hours by 11 March 2001. The X-35A was rebuilt as the X-35B, which made its first vertical takeoff and landing on 23 June 2001 and completed testing on 30 July 2001. On 9 July 2001 it performed its first in-flight conversion to hovering mode, refuelled in the air, and reached an indicated Mach 1.08 on the same sortie. On 16 July 2001 it flew a short takeoff, a transition and a vertical landing. On 20 July 2001 Major Art Tomassetti flew Mission X, and on 26 July 2001 Simon Hargreaves repeated it, and on a later flight that day landed vertically at a weight over 34,000 pounds. The contract was awarded to Lockheed Martin on 26 October 2001. The lift system’s published figures, which the LiftSystem reference gives for the production system, are a fifty-inch two-stage counter-rotating fan producing twenty thousand pounds force from twenty-nine thousand shaft horsepower, a three-bearing swivel module passing eighteen thousand pounds force and rotating ninety-five degrees in 2.5 seconds, and roll posts of 1,950 pounds force each. Those figures rest on that single encyclopaedic reference, and the 2001 company releases give the X-35B only a round total of nearly 40,000 pounds of vertical force. Published empty weights for the X-35B disagree, and none rests on a public weighing record. The takeoff-weight bracket uses the higher, the 30,697 pounds of the X-35 reference, because its excess over the X-35A agrees with the 4,000 pounds reported in 1998 for the lift fan installation. The 15,000 pound internal fuel figure matches the operational requirement of that year.
Engineering Analysis
The fan’s figure of merit of 0.697, its induced velocity of 169.3 metres per second, its mass flow of 579.2 pounds per second and its disc loading of 70.2 kilopascals follow from published geometry and performance by momentum theory. The augmentation ratio of 1.676 and the implied core mass flow of 320.2 pounds per second follow from the square-root law. The identity that a hovering jet’s dynamic pressure equals its disc loading is exact. The identity that exactly half the energy drawn through a clutch engaging a stationary inertia is destroyed is exact and independent of the torque profile. The stagnation temperature of 291.2 kelvin at Mach 1.05 and twenty-five thousand feet follows from the standard atmosphere and the energy equation. The unstick force balance shows that the record cannot pin a wing lift coefficient, since the lift system vectored to 60 degrees carries all but at most a coefficient of 0.637 at the heaviest weight in the bracket. The 26 July nozzle deflection is therefore given as a table over weight and coefficient rather than as a single angle. The minimum ground roll of 307.4 to 421.5 feet follows from the momentum balance with the nozzle aft, and the 200 foot Mission X roll in the pilot’s account is shown to be incompatible with an eighty-knot unstick at any weight in the bracket. The coefficient of 0.622 to 0.926 at the 180 knot conversion assumes sea-level density, as the momentum drag does.
The momentum drag of 5,469 pounds force at 180 knots is the fan’s mass flow times the true airspeed and is exact given that flow. The inlet temperature rise of 66.95 kelvin that consumes the hover margin is an inversion of a corrected-flow relation. The centre-of-gravity station at 47.37 percent of the fan-to-nozzle distance follows from the hover moment balance and needs no separation in metres. The canted-joint relation is exact geometry, and the finding that series joints add only when their cants alternate was established by searching the roll space rather than by derivation. The roll control power of 46.07 degrees per second squared and the residual 3.083 rest on an estimated moment of inertia and are reported across a bracket.
Every figure in this section except the series-joint search result can be recomputed from the relations and inputs the article displays, and the assumed inputs are listed in the assumptions table with what each one carries.
Inference
That Mission X was the assembly of already-demonstrated elements rather than the retirement of technical risk is an inference from the flight chronology. It is a strong one, because the programme’s own contemporary statements list every element as already flown four days earlier. That the novel event was the in-flight conversion of 9 July is an inference of the same kind. That counter-rotation was necessary rather than merely desirable is an inference from an inverted threshold calculation across a bracket of assumed roll-post positions. That the short takeoff was optional, a demonstration of technique, follows from the thrust margin of 1.232 at 34,000 pounds and is close to a deduction at that weight, but no Mission X takeoff weight is published, and at the ceiling of the bracket, empty weight plus full internal fuel, the margin is 0.9169 and the deduction fails. Under the lower published empty weight of 23,500 pounds the ceiling margin would be 1.088 and the deduction would hold across the bracket. That the conversion was the expensive event is an inference from the momentum drag, a physical force of computed magnitude, but the step from a large force to a hard piloting task has not been measured, since no workload data for these sorties is public.
What the Record Does Not Settle
Whether the fly-off would have gone the other way without Mission X is not settled and cannot be. Source selection weighs many things, the flight was three months before the decision, and no public document apportions the decision among its inputs.
Whether the X-32 could have flown an equivalent profile with more development time is not settled. Its architecture required reconfiguration as built, but the question of whether that was fundamental or contingent is a design question that was never taken far enough to answer.
Several magnitudes are not settled because the quantities they need have never been published. The clutch energies need the fan’s moment of inertia, the moment arms in metres need the fan-to-nozzle separation, the roll control power needs the roll moment of inertia, and the pitching moment of the momentum drag needs the height of the fan inlet above the centre of gravity. In every case the article gives the relation that needs none of them beside the number that does, and the assumptions table in the framing section shows which conclusions would move.
Whether the demonstration’s persuasive function should count as part of its engineering value is a question of judgement rather than fact, and this article deliberately answers it in two directions in two different sections.
Out of Scope
The production F-35 programme, its cost and schedule history, and the 2004 weight reduction effort are outside this article, which is about a demonstrator that flew in 2001. The low-observable design of either competitor is outside it. The avionics and sensor fusion that dominate the production aircraft’s reputation are outside it, because the demonstrators carried none. The carrier variant’s approach and arrestment characteristics are touched on only where they bear on the variant weight argument. The source selection process itself, and the construct-validity argument about demonstrators generally, are covered in the article on the X-32 and are not repeated here.
Conclusion
The X-35 answered the question of whether a supersonic fighter can hover without being rebuilt between the two, and the answer is yes, by carrying a fan it does not use most of the time.
The fan is worth carrying because thrust rises as the square root of mass flow at fixed power, so moving air the engine never touched multiplies vertical thrust by 1.676 without burning more fuel. It is counter-rotating because a single-rotation fan of that power would have consumed most or all of the aircraft’s roll authority just to hold a hover. Its exhaust is cold because the landing surface and the inlet both care more about temperature and pressure than about thrust, and the fan presses between half and three fifths as hard as the core does at a third of the absolute temperature. At 34,000 pounds that barrier is worth 66.95 kelvin of tolerable inlet temperature rise before the aircraft can no longer hold itself up.
Mission X, the flight the aircraft is remembered for, was not where any of that was established. Every element of it had been flown before 20 July 2001, the first in-flight conversion had happened eleven days earlier on a sortie that went faster, and the arithmetic shows that none of the three events was individually demanding for an aircraft with 41,900 pounds force of vertical thrust at the 34,000 pounds it is documented to have weighed on 26 July. No Mission X weight is published, and the short takeoff was flown by an aeroplane that, on the higher of the published empty weights, could have gone straight up unless it carried more than about three quarters of its internal fuel. The supersonic dash raised the stagnation temperature 3.1 kelvin above a standard sea-level day. The vertical landing happened at the lightest weight of the sortie, in the ordering that makes it easiest at any takeoff weight in the bracket.
And the expensive event is not among the three. Engaging the fan at the 180 knots the aircraft converted at costs 5,469 pounds force of momentum drag, which is 30.4 percent of everything the rear nozzle can produce, applied above and ahead of the centre of gravity where it pitches as well as decelerates. Nothing in the hat trick produces a step change of that size.
The sortie was a demonstration in the exact sense of the word, and the label carries no reproach. It made an architectural property legible in one flight to people who would never read a test report, and it did so honestly, because the property was real and the rival did not have it. What it was not is the experiment. The experiment was the clutch engaging in flight on 9 July, and nobody remembers the date.
References
Books
- A. W. Morley 1953, Aircraft propulsion
- Ahmed F. El-Sayed 2008, Aircraft Propulsion and Gas Turbine Engines
- Ahmed F. El-Sayed 2017, Aircraft Propulsion and Gas Turbine Engines…
- Alex P Brouwers 1980, 186 kW lightweight diesel aircraft engine design…
- Ambar K Mitra 2019, Aircraft Performance and Design
- Ben R. Rich 1994, Skunk Works
- Bert H Cooper 1980, V/STOL aircraft development
- C. Fayette Tatlor 2011, Aircraft Propulsion
- Carlos Alvarez 2010, F-35 Lightning II
- Committee on Propulsion and Energy Systems to Reduce Commercial…
- Daniel P. Raymer 1989, Aircraft Design
- David John Frederick Hopper 1990, Active control of V/Stol aircraft
- Dennis R Jenkins 2012, American X-Vehicles
- Dennis R. Jenkins 2003, American X-vehicles
- Donna McKinney 2024, F-35 Lightning II
- Frank Vann 1989, Harrier Jump Jet
- G. Geoffrey Smith 1950, Gas turbines and jet propulsion
- G. W. Hall 1985, Flight Testing the Fixed Wing Configuration of the…
- G. Warren Hall 1985, Flight testing the fixed-wing configuration of the…
- Gerard Keijsper 2007, Lockheed F-35 Joint Strike Fighter
- H. Cohen 1951, Gas turbine theory
- H. Cohen 1979, Gas Turbine Theory
- Hans Holzwarth 1912, The gas turbine
- Harry Arafi-Jones 2021, F-35 Lightning II
- Henry Cohen 1996, Gas turbine theory
- Herb Saravanamuttoo 2001, Gas turbine theory
- Hugh Harkins 2003, Lockheed Martin F-35 Joint Strike Fighter
- J. Gordon Leishman 2000, Principles of Helicopter Aerodynamics
- J. Gordon Leishman 2002, Principles of Helicopter Aerodynamics…
- J. Seddon 1990, Basic helicopter aerodynamics
- J. Seddon 2001, Basic helicopter aerodynamics
- Jack D. Mattingly 1987, Aircraft engine design
- Jack D. Mattingly 1996, Elements of gas turbine propulsion
- Jack David 2008, AV-8B Harrier jump jets
- Jack David 2008, AV-8B Harrier Jump Jets Torque Military Machines
- James C. Goodall 2021, 75 Years of the Lockheed Martin Skunk Works
- Jay Millar 1993, Lockheed’s Skunk Works
- Jay Miller 1994, Lockheed’s Skunk Works - The First Fifty Years
- Jay Miller 1995, Lockheed Martin’s Skunk Works
- John C. Ball 1977, The feasibility of the jet-flap rotor as a lift…
- John D. Andeson 1999, Aircraft Performance And Design
- John Hamilton 2012, F-35 Lightning II
- John Paul Campbell 1962, Vertical takeoff and landing aircraft
- Joseph Liston 1940, Aircraft engine design
- Joseph M.E. Liston 1942, Aircraft Engine Design
- K. Clark White 1985, Future of V/STOL aircraft systems
- Kiruba Haran 2021, Electrified Aircraft Propulsion
- Lawrence T. Russell 1997, Joint strike fighter
- Lockheed Martin 2001, Lockheed Martin Skunk Works
- Manfred Griehl 2015, Luftwaffe X-Planes
- Mayur R. Anvekar 2016, Aircraft Propulsion
- Megan Cooley Peterson 2018, F-35 Lightning II
- Mohammad H. Sadraey 2012, Aircraft design
- Multi-Panel Symposium on Fighter Aircraft Design 1977 Florence 1978…
- N. A. Cumpsty 1997, Jet propulsion
- National Aeronautics Administration 2013, American X-Vehicles An…
- Nicholas Cumpsty 2003, Jet Propulsion
- North Atlantic Treaty Organization. Advisory Group for Aeronautical…
- North Atlantic Treaty Organization. Advisory Group for Aerospace…
- North Atlantic Treaty Organization. Advisory Group for Aerospace…
- North Atlantic Treaty Organization. Advisory Group for Aerospace…
- Ole Steen Hansen 2005, The AV-8B Harrier Jump Jet Edge Books
- Otis E. Lancaster 1959, Jet propulsion engines
- Paul G. A. Cizmas 2021, Aerothermodynamics and Jet Propulsion
- peter dancey 2010, Harrier Jump Jet – A history
- Philip Terpstra 2005, V/STOL Aircraft Design
- Ralph D. Kimberlin 2003, Flight Testing of Fixed-Wing Aircraft Aiaa…
- Ronald D. Flack 2023, Fundamentals of Jet Propulsion with Power…
- S. S. Penner 1957, Chemistry problems in jet propulsion
- Saeed Farokhi 2008, Aircraft propulsion
- Saravanamuttoo 2006, Gas Turbine Theory
- Steve Pace 1992, Lockheed Skunk Works
- Steve Stone 2016, Harrier
- Top That 2004, Harrier Jump Jet
- United States Government Accountability Office 2018, Joint Strike…
- United States United States Congress 2017, Joint Strike Fighter
- United States. Dept. of Defense. 1970, Flying qualities of piloted…
- United States. National Aeronautics and Space Administration. 2022, Run…
- Volney Cecil Finch 1948, Jet propulsion turbojets
- Wayne Johnson 1980, Helicopter theory
- William G. Vogt 1988, Computer simulation of a pilot in V/STOL aircraft…
Reference
- Aerospaceweb, Lockheed Martin X-35 data
- Bevilaqua and Shumpert, propulsion system for a vertical and short takeoff and landing aircraft, United States Patent 5,209,428
- Boeing X-32
- Code One Magazine, from X to F
- Collier Trophy
- Diverterless supersonic inlet
- Hawker Siddeley Harrier
- Jenkins, Landis and Miller, American X-Vehicles
- Joint Strike Fighter programme
- Lockheed Martin account of Mission X
- Lockheed Martin team wins the Joint Strike Fighter competition, 26 October 2001
- Lockheed Martin X-35
- Lockheed Martin, F-35B succeeds in STOVL propulsion ground test, 29 May 2008
- Lockheed Martin, JSF X-35B begins vertical flight operations, 23 June 2001
- Lockheed Martin, Navy JSF breaks sound barrier, KC-10 tanker qualifications completed, 1 February 2001
- Lockheed Martin, Navy JSF completes historic flight test program, 12 March 2001
- Lockheed Martin, with weight issues resolved, F-35 focus turns to production, 14 September 2004
- Lockheed Martin, X-35B completes flight testing, 1 August 2001
- Lockheed Martin, X-35B converts to STOVL and goes supersonic in the same flight, 10 July 2001
- Lockheed Martin, X-35B vertical landing from wingborne flight, 16 July 2001
- Momentum theory for an actuator disc
- Paul Bevilaqua
- Pratt and Whitney F119
- Rolls-Royce LiftSystem
- Short takeoff and vertical landing
- The X-35B in the National Air and Space Museum collection
- Tirpak, Scoping Out the New Strike Fighter, Air Force Magazine, October 1998
- Tomassetti, Above and Beyond, Mission X, Air and Space Smithsonian, May 2002
- Yakovlev Yak-141
Related Post
- X-Planes: Aerojet X-8 Aerobee
- X-Planes: Bell X-1
- X-Planes: Bell X-14
- X-Planes: Bell X-16
- X-Planes: Bell X-2
- X-Planes: Bell X-22
- X-Planes: Bell X-5
- X-Planes: Bell X-9 Shrike
- X-Planes: Bensen X-25
- X-Planes: Boeing X-20 Dyna-Soar
- X-Planes: Boeing X-32
- X-Planes: Convair X-11
- X-Planes: Convair X-12
- X-Planes: Convair X-6
- X-Planes: Curtiss-Wright X-19
- X-Planes: Douglas X-3 Stiletto
- X-Planes: Framing and the Research Aircraft Model
- X-Planes: Grumman X-29
- X-Planes: Hiller X-18
- X-Planes: Lockheed Martin X-33
- X-Planes: Lockheed X-17
- X-Planes: Lockheed X-27
- X-Planes: Lockheed X-7
- X-Planes: Martin Marietta X-23 PRIME
- X-Planes: Martin Marietta X-24
- X-Planes: North American X-10
- X-Planes: North American X-15
- X-Planes: Northrop X-21
- X-Planes: Northrop X-4 Bantam
- X-Planes: Orbital Sciences X-34
- X-Planes: Osprey X-28 Sea Skimmer
- X-Planes: Rockwell X-30 and the National Aero-Space Plane
- X-Planes: Rockwell-MBB X-31
- X-Planes: Ryan X-13 Vertijet
- X-Planes: Schweizer X-26 Frigate
Research
- A Canadian Light Fighter 1940
- A Novel Sliding Mode Controller for Underactuated Vertical Takeoff and Landing Aircraft 2020
- A Prediction Method for Deck Motion of Aircraft Carrier Based on Particle Swarm Optimization and Kernel Extreme Learning Machine 2017
- Aa. Madsen 2024
- Aaron et al 2003
- Abbas and Riggins 2016
- Abdol-Hamid et al 2018
- Abdullah and Schlattmann 2016
- Abe 2023
- Abedi et al 2020
- Abercrombie 1979
- Abergo et al 2026
- Aboelezz et al 2022
- Abraham et al 2023
- Abras and Hariharan 2018
- Abrego et al 2002
- Abryandoko et al 2026
- Acheson 2011
- Acierno and Merzari 2022
- Adamson 1968
- Adelt 1983
- Adibhatla 1993
- Adibhatla 1994
- Adjei and Fan 2024
- Adkins and Sherwood 1996
- Advanced Short Takeoff and 1995
- Advances in Aircraft Gear System Technology 1992
- Advisory Group for Aerospace Research and Development 1996
- Aerodynamics of Power Plant 1981
- Afridi et al 2023
- Afridi et al 2024
- Afroz and Sharif 2020
- Afsar et al 2019
- Agarwal and Deese 1986
- Ageev and Pavlenko 2016
- Aggarwal 1986
- Agrell and Elmeland 1984
- Ahmed et al 2025
- Ahmed Snikdha and Chen 2023
- Ahn et al 2023
- Ahuja and Litherland 2023
- Ahuja and Mavris 2020
- Ahuja et al 2026
- Ai et al 2018
- Ai et al 2020
- Ai et al 2021
- Ai et al 2021
- Ai et al 2025
- Aidala 1985
- Aillaud et al 2016
- Aillaud et al 2017
- Air Force Test Pilot School Edwards Afb Ca 1969
- Aircraft Research and Technology 1980
- Aircraft Ship Operations 1991
- Akagi et al 1997
- Akash et al 2023
- Akashi et al 1996
- Akatsuka 2026
- Aktas 2015
- Akturk and Camci 2022
- Alavi Moghadam et al 2017
- Alavilli and Kadhar Maideen 2021
- Ale Isaac Khoueini
- Alendar et al 2022
- Alexander et al 1986
- Algorithm for selecting UAV’s electric propulsion system parameters based on flight route 2015
- Ali and Al-Shamma 2026
- Ali and Asiri 2022
- Ali et al 2017
- Allen 2004
- Allenspach and Ducard 2021
- Alperin and Wu 1983
- Alperin and Wu 1983
- Alquist et al 1953
- Alscher et al 1966
- Altamirano et al 2023
- Alwi et al 2015
- Amato et al 2022
- Ames 1975
- Amin and Aijun 2017
- Amping Airpower-Electric Vertical Takeoff 2024
- Amri et al 2016
- Amuedo et al 1989
- Amundson and Holm 1989
- An et al 2025
- An H infinity loop-shaping design 2000
- Analysis of Flow Field Distortion in Ship Inlet System and Its Effect on Compressor Performance 2024
- Analysis of the relationship between mass, speed and cost of an unmanned aircraft 2024
- Anantha et al 2024
- Ananthakrishnan et al 2019
- Anderson 1960
- Anderson 1979
- Anderson 1983
- Anderson 1984
- Anderson 1989
- Anderson and Bradley 1987
- Anderson and Foster 1984
- Anderson and Gibb 1996
- Anderson and Schroers 1972
- Anderson et al 1983
- Anderson et al 2024
- Andersson et al 2026
- Andrejczyk 2023
- Andrew 1972
- Andrew and Cahn 1967
- Andrianantara et al 2021
- Andriani and Ghezzi 2002
- Antl 1970
- Antonakis and Biannic 2024
- Antonov and Fomin 2024
- Antonov et al 2025
- Antošová and Trávníček 2022
- Aouf et al 2002
- Aphale et al 2004
- Appleton et al 2021
- APPLICATION OF FLUIDIC THRUST VECTORING IN V/STOL AIRCRAFT 2024
- Arabshahi and Whitfield 1995
- Arias et al 2021
- Arias et al 2023
- Arias et al 2025
- Arias et al 2025
- Arledge et al 1996
- Armstrong and Levine 1988
- Armutcuoglu et al 2004
- Arnaiz 1975
- Aroussi 2026
- Arrouk et al 2018
- Asai 1994
- Asai 1995
- Ascani 1974
- Ashkenas 1965
- Asiatico et al 2026
- Askari and Abedi 2026
- Askari and Soltani 2017
- Askari and Soltani 2019
- Askari and Soltani 2020
- Askari and Soltani 2023
- Askari et al 2018
- Asri et al 2019
- Assessing Competitive Strategies for 2001
- Atencio et al 1973
- Athanasakos et al 2020
- Atkinson et al 2013
- Aujogue et al 2022
- Aukerman 1991
- Aulehla and Besigk 1982
- Aulehla and Kissel 1982
- Aungier 1995
- Autelitano et al 2016
- Avant et al 2018
- Avanzini and Matteis 1995
- Awad and Stumpf 2022
- Axelson 1975
- Axelson and Upton 1970
- Axten and Johnson 2020
- Axten and Johnson 2021
- Aydin et al 2025
- Azevedo and Galdino da SIlva 2016
- Azevedo et al 1990
- Açıkgöz and Aslan 2016
- Baals et al 1970
- Baban et al 1990
- Babcock and Mani 2015
- Babcock and Mani 2017
- Babcock et al 2019
- Babinsky 2014
- Babčan and Janovec 2021
- Bach and McNally 1988
- Bachelder et al 2002
- Back et al 1972
- Baer-Riedhart 1982
- Bagai and Leishman 1992
- Baggi et al 2020
- Baggi et al 2022
- Bahr et al 2021
- Bai et al 2022
- Bai et al 2024
- Bai et al 2025
- Bai et al 2025
- Baigunchekov et al 2021
- Bailey 1972
- Bailey and Starr 1976
- Bailey et al 1979
- Baker 1966
- Bakhle et al 2018
- Balaban and Erdem 2022
- Balakrishnan and Srinivasan 2016
- Balch 1985
- Baldini et al 2020
- Ball 1966
- Ball 1974
- Ball 1979
- Ball and Atkins Jr 1978
- Ball and Ross 1971
- Ballard et al 1980
- Balusamy et al 2024
- Banazadeh and Saghafi 2016
- Banazadeh and Taymourtash 2016
- Bando et al 1993
- Bandopadhyay and Mistry 2019
- Bandopadhyay and Mistry 2022
- Bangert et al 1982
- Bangert et al 1983
- Bangert et al 2017
- Bao et al 2020
- Bao et al 2021
- Barakos et al 2020
- Barankiewicz 1991
- Barankiewicz 1993
- Barankiewicz et al 1992
- Barankiewicz et al 1994
- Barata 1991
- Barata et al 1993
- Bardera and Matías-García 2022
- Bardera-Mora et al 2016
- Bardera-Mora et al 2019
- Barnes et al 1984
- Barnhart 1989
- Baron 1983
- Baron 2015
- Barr et al 2018
- Barr et al 2020
- Barra et al 2020
- Barrett 1965
- Barron and An 1996
- Barrows 1980
- Barry 1971
- Barry et al 2023
- Basgall et al 2020
- Bates et al 2000
- Bates et al 2003
- Bath et al 2021
- Bath et al 2022
- Bath et al 2023
- Batterton and Blaha 1987
- Batther et al 2026
- Battiston et al 2025
- Bauer 1987
- Bayati and Williston 1977
- Baydar et al 2018
- Baz and Chen 1993
- Beach et al 2024
- Beale 1986
- Beale and Miller 1975
- Beals 2018
- Beals et al 2026
- Beans 1995
- Bear et al 1979
- Beard and Foley 1982
- Beard and Foley 1983
- Beatty and Riccius 1983
- Beaubert and Viazzo 2002
- Beaufrere 1988
- Beaumier et al 2001
- Bedford 1962
- Bedke and Gorrell 2021
- Beeler 1965
- Beeler and Russell 1964
- Beeler and Volk 1965
- Beermann et al 2015
- Behavior Patterns of Three Archetypal Arms Suppliers Based on Empirical Media Analysis of the First Korean Fighter Jet Program 2022
- Behbahani et al 2016
- Behnke et al 2022
- Behrouzi and McGuirk 1999
- Behrouzi and McGuirk 2000
- Behrouzi and McGuirk 2000
- Beilman 1983
- Beisbier 2002
- Bell Aerospace Co Buffalo Ny 1955
- Bell Aerospace Co Buffalo Ny 1970
- Bell and Pringle 1996
- Belluomini et al 2023
- Bemporad et al 2001
- Bemporad et al 2001
- Bendarkar et al 2021
- Benmoussa and Gamboa 2023
- Bennett 1984
- Benser et al 1975
- Benson and Anderson 1983
- Bento et al 2020
- Benyamen and Keshmiri 2022
- Benzakein and Kazin 1971
- Berens 2019
- Berg et al 1988
- Bergman 1948
- Bergman 1979
- Berman and Andersen 1996
- Bernal and Sarohia 1983
- Bernal and Sarohia 1984
- Bernard et al 2000
- Bernstein 1997
- Berrier 1983
- Berrier and Re 1978
- Berry 1982
- Berry and Harris 2024
- Berry and Schweikhard 1976
- Berry and Speakman 1993
- Bertelsen 2016
- Berthold et al 2017
- Berton et al 2000
- Beschorner et al 2025
- Bettner and Elrod 1982
- Beveridge 1974
- Bevilacqua and Dejoode 1979
- Bevilaqua 1974
- Bevilaqua 1977
- Bevilaqua 1984
- Bevilaqua 1987
- Bevilaqua 1996
- Bevilaqua 1997
- Bevilaqua 2009
- Bevilaqua 2009
- Bevilaqua 2023
- Bevilaqua and Lee 1980
- Bezerra and Santos 2022
- Bhabar and Mukesh Sharma 2025
- Bhagwat 2013
- Bhagwat and Sridharan 2016
- Bhandari and Chakraborty 2026
- Bhandari and Chakraborty 2026
- Bhandari et al 2023
- Bhandari et al 2024
- Bhardwaj and Holzapfel 2024
- Bhatra and Mishra 2023
- Bhunia et al 2026
- Bian et al 2025
- Biczó et al 2020
- Bielat 1959
- Biesiadny 1991
- Biesiadny et al 1993
- Bilen and Yavuz 2023
- Bingham and Noonan 1975
- Binney et al 2003
- Binwen Lu et al 2016
- Biot 1949
- Birckelbaw 1992
- Birckelbaw and Nelson 1992
- Birckelbaw et al 1994
- Birckelbaw et al 1995
- Bird et al 1991
- Birkler 2001
- Bishop et al 2000
- Bittrick 1984
- Blackman and Eigenmann 1981
- Blaesser et al 2024
- Blaha and Batterton 1990
- Blaha et al 2023
- Blake and Laughrey 1987
- Bland 1971
- Bland and Konsewicz 1976
- Bland et al 1976
- Blanken and Whalley 1993
- Blevins and Wagner 2000
- Blinkhorn 1948
- Block et al 1986
- Bludau et al 2017
- Blumenthal et al 2018
- Bodden and Virnig 1994
- Bode et al 1978
- Bodson 2000
- Boelens 2017
- Bogar et al 1985
- Bogdan 2015
- Bohne and Niehuis 2004
- Bohorquez and Pines 2003
- Boland et al 1993
- Bolanovich and Marks 1959
- Boldman et al 1991
- Boles and Stockman 1979
- Boles et al 2021
- Bolin et al 2015
- Bolt 1980
- Bond and Key 2025
- Bond et al 2001
- Bonnin and Hoogreef 2025
- Bonnin et al 2023
- Boothe 1971
- Boppe 1978
- Boppe and Aidala 1980
- Boraas and Ashby 1969
- Borcherding et al 2023
- Borchers et al 1992
- Borer et al 2017
- Boretti 2023
- Boretti 2024
- Boretti 2024
- Boruff and Roch 1981
- Bossler and Robert B. 1965
- Bottorff 2004
- Boulkeraa et al 2022
- Bowden and Shockey 1970
- Bowers 1979
- Bowers and Buchan 1978
- Bowling et al 1969
- Bowman et al 2018
- Boyer and O’Brien 2002
- Bozeman 2023
- Bozeman 2024
- Brady and Gururajan 2025
- Brady and Gururajan 2026
- Brahma Nand Agrawal et al 2024
- Braman et al 1983
- Brandau 1965
- Brandt 2018
- Braun and Podleski 2019
- Bravo et al 2021
- Bravo Mosquera et al 2019
- Bray and Knowles 1989
- Bray and Knowles 1990
- Brehm et al 2015
- Brehm et al 2017
- Brelje and Martins 2018
- Brenner et al 2023
- Breton et al 2017
- Breugelmans 1975
- Breugelmans 1975
- Breul 1963
- Bright and Simon 1992
- Britcher and Baris 2023
- Brodsky 1970
- Bronz 2019
- Brooks et al 1976
- Brower 1989
- Brown 1950
- Brown 1965
- Brown 1978
- Brown 1989
- Brown and Fischer 1967
- Brown and Fisher 1968
- Brown and Hagen 2017
- Brown et al 2009
- Brown et al 2019
- Bruce and Rytting 1983
- Bruschewski et al 2025
- Bryce et al 1993
- Bryson 1971
- Buchholz 2002
- Bucknell 1987
- Bucknell et al 1990
- Buffington 1999
- Buffington 1999
- Buffington and Buffington 1997
- Buffum and Robertson 1967
- Bugliari Armenio et al 2024
- Bulat and Minin 2017
- Bulat and Minin 2018
- Bunda et al 1972
- Burcham and Batterton 1976
- Burcham et al 1990
- Burcham et al 1990
- Burgan 1984
- Burger 1983
- Burger 1986
- Burger et al 1975
- Burger et al 1979
- Burley 1971
- Burnes et al 2001
- Burr 1968
- Burris 1966
- Burroughs 1965
- Bursey and Dickinson 1990
- Burstadt et al 1971
- Burt et al 2019
- Busch et al 2015
- Bushnell 1990
- Butler 1964
- Butler et al 1966
- Buyukataman and Kazerounian 1998
- Bye 1993
- Bykerk et al 2022
- Byrnes et al 1974
- Cacciola and Calabria 2026
- Caffee 1985
- Cai and He 2017
- Cai et al 1990
- Cai et al 2017
- Cai et al 2019
- Cai et al 2023
- Calarese and Walterick 1978
- Caldwell and Lafavor 1980
- Calise and Kramer 1982
- Caliskan and Hajiyev 2003
- Calogeras 1969
- Calvano and Harney 1998
- Calvert 1997
- Calvert and Stapleton 1993
- Camacho 1991
- Cameron et al 2016
- Campbell 1960
- Campbell 1974
- Campbell and Ellis 1970
- Campbell and Quinn 1974
- Campbell and Syberg 1984
- Campbell et al 1977
- Campbell et al 1978
- Campbell et al 1985
- Campos 2001
- Candee 1943
- Canfield et al 1994
- Cangioli et al 2018
- Canteenwalla and Chishty 2017
- Cao 1999
- Cao and Su 2003
- Cao et al 2020
- Cao et al 2022
- Cao et al 2022
- Cao et al 2023
- Cao et al 2024
- Cao et al 2024
- Capece and Fleeter 1984
- Capello et al 2019
- Capone 1975
- Capone 1979
- Capone and Reubush 1983
- Capone et al 1984
- Cappetta 1993
- Car et al 2000
- Cardenas 2022
- Carico and Garcia-Otero 1995
- Carlin and Blair 1983
- Carlin and Hastings 1978
- Carlson and Zhao 2002
- Carlyle 1976
- Carpenter and Cizmas 2017
- Carpenter and Cizmas 2017
- Carpenter and Gotlieb 1970
- Carpio-Alemán et al 2016
- Carr 1984
- Carreno Ruiz et al 2024
- Carrier et al 2001
- Cartieri et al 2018
- Cassaro et al 2018
- Cassetti 1978
- Cassinelli et al 2023
- Castells and Mishler 1973
- Catalano et al 1977
- Caton and Franke 1991
- Caudle et al 2025
- Cavage 1975
- Cavage 1975
- Cenbo et al 2015
- Centracchio et al 2018
- Cerbe and Reichert 1989
- Cha and Kinnas 2022
- Chace 2015
- Chachada et al 2016
- Chaderjian 2022
- Chaderjian et al 2002
- Chaderjian et al 2002
- Chaderjian et al 2002
- Chadsey and Yechout 2001
- Chai et al 1995
- Chaitanya et al 2025
- Chakraborty 2019
- Chakraborty and Mishra 2021
- Chakraborty and Mishra 2022
- Chakraborty and Mishra 2023
- Chakraborty and Mishra 2023
- Chakraborty et al 1990
- Chakraborty et al 2022
- Chakraborty et al 2023
- Challier and Hey worth 1964
- Chaloff et al 1974
- Chamberlain 1968
- Chamehsara and Karami 2020
- Chana 2002
- Chance Vought Corp Dallas Tx 1979
- Chandler and Montes 2019
- Chandrasekharan 1988
- Chang 2015
- Chang and Hsu 1960
- Chang et al 2018
- Chang et al 2022
- Chao and van Dam 2004
- Chaparro et al 2016
- Chapman 2018
- Chapman 2018
- Chapman 2018
- Chapman 2018
- Chapman 2018
- Chapman 2018
- Chapman 2019
- Chapman 2023
- Chapman et al 2025
- Chattopadhyay et al 1992
- Chauhan and Martins 2020
- Chaussee 1978
- Chavez et al 2017
- Cheatham et al 1990
- Cheatham et al 1991
- Chen 1992
- Chen 1998
- Chen 2017
- Chen and Bossler 1995
- Chen and Hubner 2020
- Chen and Liao 2018
- Chen and Liao 2020
- Chen and Tan 2019
- Chen and Voulgaris 1998
- Chen and Zhang 1983
- Chen et al 2004
- Chen et al 2018
- Chen et al 2018
- Chen et al 2018
- Chen et al 2019
- Chen et al 2021
- Chen et al 2023
- Chen et al 2025
- Chen et al 2025
- Chen et al 2026
- Chen et al 2026
- Chen et al 2026
- Cheney 1988
- Cheng and Pei 2020
- Cheng and Pei 2021
- Cheng and Pei 2022
- Cheng et al 1973
- Cheng et al 2018
- Cheng et al 2020
- Cheng et al 2025
- Chennuru et al 2025
- Chernyshenko and Privalov 2004
- Cherrett et al 1994
- Cherrett et al 1994
- Cherrett et al 1995
- Cherrett et al 1995
- Chi et al 2022
- Chiappinelli et al 2019
- Chiaverini et al 1990
- Chidambaram and Vinoth Raj 2025
- Chien 1975
- Childs 1991
- Childs et al 1987
- Childs et al 1992
- Chilukuri 2020
- Chima 1991
- Chin 1988
- Chinwicharnam et al 2015
- Chiocchia and Pignataro 1995
- Chiozzotto 2017
- Cho 2025
- Choe and Kim 2016
- Choe et al 2002
- Choe et al 2020
- Choi and Lee 2018
- Choi et al 2022
- Choi et al 2025
- Choi et al 2025
- Choi et al 2026
- Chopra et al 2022
- Chotalia and Alone 2017
- Chou and Hwang 1984
- Chouicha et al 2019
- Chouicha et al 2020
- Chow 1993
- Chu 1980
- Chun and Swanson 1964
- Chung 2004
- Chung et al 1993
- Chung et al 1993
- Chung et al 1995
- Chung et al 1995
- Chung et al 1997
- Cimbala et al 1987
- Cimbala et al 1988
- Cinquegrana and Vitagliano 2021
- Citavý 1992
- Clark 1965
- Clark 1974
- Clark 1975
- Clark 1980
- Clark 1984
- Clark 1995
- Clark and Smith 1965
- Clark and Vasta 1984
- Clark and Walters 1986
- Clark et al 1982
- Clauser 1954
- Cleveland 1970
- Cliff et al 1982
- Cloos and Nelson 1990
- Clough 1990
- Clymer and Flora 1973
- Cochrane and Boissevain 1978
- Coder et al 2017
- Coder et al 2018
- Coe and Riley 1988
- Coen and Foss 1985
- Cohan and Hirsh 1966
- Colbourne 1972
- Cole 1988
- Cole 2025
- Coleman et al 1996
- Coles 1968
- Collins 1970
- Collins Jr 2005
- Colpin 1979
- Comesana et al 2026
- Commander 1964
- Compton and Bowers 1983
- Computational and Experimental Analysis of Optimized Dual Throat Fluidic Thrust Vectoring Nozzle Configurations 2024
- COMPUTER-AIDED SYSTEM OF AIRCRAFT WEIGHT DESIGN 2018
- Comunian et al 2025
- Conceptual design of a 1973
- Conference on V/Stol Aircraft 1960
- Configuration Design and Workspace Analysis of Parallel Mechanism Driven by Eight Cables for On-orbit Assembly 2021
- Conlon and Bowles 1977
- Conlon and Bowles 1978
- Connelly 1982
- Conner and Wellman 1994
- Conners 1992
- Conners 1993
- Conners 1995
- Conners and Sims 1998
- Connolly et al 2018
- Conti et al 1992
- Control authority assessment in aircraft conceptual design 1993
- Control system design using frequency domain models and parameter optimization with application to supersonic inlet controls 1976
- Cook 1976
- Cook 1993
- Cook and Hauser 2018
- Cook and Hickey 1967
- Coolican 2002
- Coons 1987
- Coopmans et al 2022
- Copenhaver and Okiishi 1989
- Coplin 1966
- Cordeaux 1991
- Corle et al 2019
- Corliss and Sprysl 1999
- Corliss et al 1977
- Corliss et al 1978
- Cormier 1979
- Cornelius et al 2021
- Corsiglia et al 1989
- Cosenza and Kummeth 1974
- Cosgrove and Ryan 1969
- Cosgrove et al 1968
- Coty and Kesling 1967
- Courtin and Hansman 2019
- Cousins and Obrien 1985
- Cousins et al 2026
- Coustols et al 1997
- Covert 1984
- Coward 1955
- Cowell 1947
- Cox and Abbott 1966
- Cox and Kirby 1986
- Cox and Roskam 1990
- Crafa and Reed 1980
- Crafton et al 1999
- Crafton et al 2017
- Craig 1965
- Crandall et al 1973
- Crimi 1965
- Crites et al 1992
- Crossley 2004
- Crossley and Rutherford 1995
- Crosthwait 1970
- Crowe and Martin 2019
- Crowell and Myers 2016
- Crown 1950
- Csank and Connolly 2015
- Csank and Zinnecker 2014
- Cui et al 2019
- Cui et al 2021
- Cui et al 2025
- Culpepper et al 2021
- Cummings and Hall 2002
- Cunningham and Boytos 1981
- Cunningham and Boytos 1983
- Cunningham and Boytos 1988
- Cunningham et al 2022
- Curry et al 1965
- Curtis 2002
- Curtis and Penrose 1993
- Curtiss 1965
- Curtiss 1970
- Curtiss 1971
- Curtiss and Howard C. 1969
- Cusanelli and Slutsky 2008
- Cusati et al 2023
- Cusator et al 2024
- Cybyk et al 1995
- Cyrus 1990
- Cyrus 1998
- Da et al 2020
- Dababneh and Kipouros 2018
- Dai et al 2019
- Dai et al 2026
- Daidzic 2016
- Dailey 1955
- Daliri et al 2018
- Dang 2026
- Daniels et al 1989
- Dantsker et al 2018
- Dantsker et al 2019
- Darlow and Vance 1974
- Darmstadt and Robuck 2018
- Darmstadt et al 2021
- Das and Trippi 1989
- Das et al 2024
- Das et al 2025
- Dasgupta 2002
- Dau et al 1965
- Daud Filho and Belo 2023
- Davanlou et al 2026
- Davenport et al 1972
- Davenport et al 1974
- Davenport et al 1985
- Davidson et al 1972
- Davies and Halliday 2024
- Davis 1972
- Davis 1973
- Davis 2011
- Davis and Ela 1969
- Davis and Hines 1976
- Davis and Park 2017
- Davis and Spicer 1965
- Day et al 1983
- de Castro and Brembeck 2019
- de Castro and Brembeck 2021
- de Haan et al 2023
- De Lucena et al 2022
- de Matteis et al 1998
- de Paula et al 2017
- de Paula et al 2025
- De Persis et al 2001
- de Rosa et al 2022
- de Souza and Ciloni 2021
- de Vries and Van Kampen 2019
- de Vries and Vos 2022
- de Vries et al 2019
- Dean 1979
- Dean et al 2018
- DeBardelaben and Sreenivas 2022
- DeCastro et al 2008
- Decker 1966
- Decoupling Inversion Tracking Control of Underactuated Vertical Takeoff and Landing Aircraft 2024
- Deere and Hunter 1999
- Deere et al 2003
- Deere et al 2007
- Deere et al 2017
- Defense Acquisition Univ Ft Belvoir Va 2004
- Defense Science Board Washington Dc 1979
- Degang and Xiang 2020
- Dehnavi et al 2023
- DeHoff 1979
- Dejene Toge and Pradeep 2015
- DeJesus 2013
- Del Bianco et al 1997
- Dela Peña 2025
- Della Corte et al 2021
- Dellacorte and Steinetz 1992
- Delorme et al 2021
- Dement 1990
- Deng and Ren 2017
- Deng and Tao 2025
- Deng et al 2018
- Deng et al 2020
- Deng et al 2024
- Denham 2002
- Denham and Paines 2008
- Denisenko et al 2021
- Denner et al 1998
- Denning 1962
- Denning and Mitchell 1986
- Dennis et al 1993
- Denton and Xu 2002
- Derakhshan et al 2024
- Derlaga and Morrison 2017
- Derlaga and Morrison 2018
- Derrouaoui et al 2023
- Desai et al 1977
- Design and Aerodynamic Analysis of a VTOL Tilt-Wing UAV 2021
- Design and Kinematic Analysis of Automatic Articulated Robot 2022
- Design and Theoretical Analysis of Single Plate Clutch by Varying Friction Lining Materials 2015
- Design concepts for minimizing hot-gas ingestion in V/STOL aircraft 1981
- Design definition study of 1975
- Design of the circulation control wing STOL demonstrator aircraft 1979
- Design Principles and Methods 1999
- Desilets
- DeSmidt et al 2013
- DeSmidt et al 2018
- Destarac and van der Vooren 2004
- Deveaux 1965
- DeVita and Quenneville 1994
- Dewispelare and Stager 1981
- Dhruw et al 2022
- Di et al 2025
- Dias et al 2025
- Diaz et al 2019
- Dickman and Takahashi 2016
- Diecke 2023
- Diedrich 1971
- Diedrich 1975
- Diedrich et al 1972
- Diekmann 2017
- Digges 1971
- Digital Engine Control for V/STOL and V/TOL Aircraft 1982
- Dijkstra et al 1997
- Dikbas and Atik 2018
- DiMaggio et al 2025
- Dinca et al 2019
- Ding et al 2016
- Ding et al 2025
- Dinh and Kim 2021
- Dinh et al 2017
- Divakar and Rajalakshmi Samaga 2022
- Dixon and Hunsaker 2023
- Dobek 1973
- Doblhoff 1956
- Dodic et al 2023
- Doff-Sotta et al 2025
- Dogga and Turner 2023
- Doherty et al 2018
- Dolan 1964
- Dollyhigh 1970
- Dollyhigh et al 1984
- Doman and Oppenheimer 2002
- Domel 2015
- Domel 2015
- Domel 2017
- Domel 2017
- Domel 2019
- Donaldson et al 1966
- Donaldson et al 1971
- Donelson et al 1989
- Dong et al 2020
- Dong et al 2021
- Dong et al 2022
- Dong et al 2025
- Dong et al 2025
- Doo et al 2021
- Doonan and Kuchar 1992
- Dorfling and Traub 2023
- Dorr et al 1992
- Dos Santos et al 2024
- Dosanjh and Montegani 1968
- Douglas et al 1990
- Dowdle et al 2018
- Doyle and Dixon 1962
- Doğru et al 2016
- Drago 1985
- Drago and Mack 1987
- Drinkwater and Rolls 1962
- Drinkwater et al 1965
- Drummond 1989
- Drummond and Barankiewicz 1990
- Druzhinin et al 2017
- Druzhinin et al 2018
- Du et al 2023
- Du et al 2025
- Duan and Okwudire 2018
- Duan et al 2024
- Dub et al 2016
- Dubois et al 2016
- Ducard and Carughi 2024
- Ducted fan
- Dudley 1986
- Dudley et al 1981
- Dudley et al 1990
- Duffy and Jansen 2018
- Dugan 1972
- Dugan et al 1971
- Dugas 1968
- Dukes 1970
- Dukhnovskiy 2023
- Dunaevskii et al 2020
- Dunbar et al 2002
- Dundore and Schneider 1968
- Dunn and Emery 1966
- Duong et al 2020
- Durali and Kerrebrock 1998
- Durston and Smith 1981
- Durston and Stonum 1987
- Durston and Stonum 1988
- Dutton 1967
- Dutton 1987
- Dwarakanath et al 1992
- Dwinger and Friedrichs 2017
- Dyke 1963
- Dyson 2018
- Dyson 2023
- Eames and Mason 1988
- Ebus and Dietz 2020
- Ebus et al 2022
- Echavarria and Poroseva 2015
- Echigo et al 2019
- Economou et al 2019
- Editor 2016
- Editor 2016
- Effect of inlet Mach number on performance and flow structure of an axial supersonic through-flow fan cascade 2023
- Egawa 1956
- Egerton and Fitzpatrick 1967
- Eick and Liu 1996
- Eigenmann et al 1984
- Eilertson 1975
- Eilertson 1977
- El 1983
- El-Okda and Telionis 2002
- El-Salamony and Teperin 2020
- Elahi Kahooker and Liu 2026
- Elbasueny et al 2019
- Elbir and Üçgül 2026
- Eldridge et al 1973
- Ellenrieder and Brinson 1998
- Eller 1994
- Elliott 1976
- Elliott and Schreiber 1964
- Elliott and Simmons 1987
- Elliott et al 1990
- Elmendorf et al 1995
- Emanuel 1984
- Eminton and Lord 1956
- Emmerson 1998
- Enenakpogbe et al 2024
- Enenakpogbe et al 2025
- Engelbrecht et al 2022
- Engelland 1991
- Enghardt et al 2019
- Englar 1974
- Englar 1975
- Englar 1987
- Englar 1988
- Englar and Campbell 2002
- Englar and Campbell 2002
- Englar and Huson 1984
- Englar and Kirkpatrick 1969
- Englar et al 1977
- Enns 2003
- Envia 2016
- Enzinger 1988
- Erdos et al 1976
- Erkaya et al 2016
- Erturk and Gomec 2020
- Erwin and Vitale 1972
- Erwin et al 1964
- Eshleman et al 1986
- Eshlemen 1985
- Esker and Debonis 1991
- Esker and McArdle 1993
- Esker and Roddiger 1979
- Esker and Sedrick 1972
- Esquieu 2003
- Essomba and Nguyen Vu 2018
- Evangelista et al 2023
- Evans and Chamblee 1966
- Experimental Investigations on the Strut Controlled Thrust Vectoring of a Supersonic Nozzle 2020
- Eyles et al 2002
- F119 Nozzle Flaps Tested 2005
- Fabri and Le Grives 1960
- Faidh-Allah 2018
- Fan and Li 2019
- Fan et al 2015
- Fan et al 2017
- Fan et al 2018
- Fan et al 2020
- Fan et al 2022
- Fan et al 2024
- Fan et al 2024
- Fan et al 2025
- Fan et al 2026
- Fan et al 2026
- Fan et al 2026
- Fancher 1971
- Fanucci et al 1969
- Far-field noise and internal modes from a ducted propeller at simulated aircraft takeoff conditions 1992
- Fardin et al 2026
- Faria et al 2018
- Farley 1968
- Farley 1971
- Farokhi 1998
- Farr 1973
- Farris et al 1983
- Farsi and Rosen 2023
- Farzad and Yagoobi 2019
- Fasching and Kutney 1964
- Faye 1960
- Fazeli Asl and Moosapour 2017
- Feddersen and Cea 1977
- Federspiel 1979
- Feil et al 2016
- Feil et al 2019
- Fejtek and Roberts 1992
- Felder et al 2022
- Felker and Light 1988
- Felker et al 1986
- Fellenstein et al 1996
- Fellers and Patierno 1970
- Feng 2016
- Feng and Song 2017
- Feng et al 1999
- Feng et al 2001
- Feng et al 2003
- Feng et al 2003
- Feng et al 2003
- Feng Lin et al 1999
- Fengyu Jin et al 2018
- Fennell and Black 1982
- Fenwick 1966
- Fenwick 1967
- Ferdaus et al 2021
- Ferlauto and Marsilio 2016
- Fernando et al 2026
- Feroskhan et al 2025
- Ferrar et al 2016
- Ferrier et al 2024
- Fielding 1982
- Fielding and Lodge 2000
- Figge and Bernhardt 1975
- Figueira et al 2025
- Filinov and Ostapyuk 2019
- Filippoli 2026
- Final Assembly and Checkout 2002
- Finger et al 2018
- Finger et al 2020
- Finger et al 2020
- Fink and Lastinger 1961
- Finseth et al 1988
- Firnhaber Beckers et al 2023
- Firoozian et al 1991
- Fishbach and Franciscus 1982
- Flamm 1998
- Flamm et al 2007
- Flanagan and Jarrett 2023
- Flanders 1970
- Flax 1995
- Fletcher 1962
- Fletcher and Burns 1979
- Flight Test Data Analysis of Hybrid Vertical Take-off and Landing Unmanned Aerial Vehicle 2016
- Flight Test Programme 1970
- Flight-test evaluation of engine power effects on lift and drag 1985
- Flores et al 1988
- Flores et al 1989
- Florio et al 2019
- Flow Field Analysis of Different Intake Bump (Compression Surface) Configurations on a Supersonic Aircraft 2017
- Flow visualization studies of the internal flow characteristics in asimulated mixed flow vectored thrust ASTOVL engine configuration 1991
- Fluk 1981
- Fluk and Wu 1983
- Fogleman et al 2026
- Foley and Woodrey 1980
- Foltz 1962
- Ford 1973
- Ford 1998
- Foss 1979
- Foss and Kleis 1976
- Foster et al 1987
- Fourie and Jones 2015
- Fournis 2022
- Fox et al 1974
- Fozard 1978
- Fozard 1979
- Fozard 1986
- Fradenburgh et al 1973
- Fraiser 1960
- Franciscus 1983
- Franciscus and Luidens 1984
- Franck and Dillard 2006
- Franck and Udis 2015
- Franck et al 2012
- Franke and Unnever 1985
- Franklin 1986
- Franklin 1993
- Franklin 1993
- Franklin 1993
- Franklin 1994
- Franklin 1996
- Franklin 1997
- Franklin 1997
- Franklin 2000
- Franklin and Anderson 1984
- Franklin and Engelland 1991
- Franklin and Engelland 1993
- Franklin and Innis 1972
- Franklin and Innis 1974
- Franklin and Innis 1977
- Franklin and Innis 1978
- Franklin and Innis 1980
- Franklin and Stortz 1989
- Franklin and Stortz 1993
- Franklin et al 1986
- Franklin et al 1988
- Franklin et al 1989
- Franklin et al 1990
- François et al 2020
- Frascella et al 2016
- Frazzini 1970
- Frederick et al 2021
- Fredericks et al 2013
- Fredericks et al 2015
- Fredericks et al 2016
- Fredrickson 1974
- Fredrickson et al 1972
- Freeman and Klunk 2018
- Freudenstein et al 1984
- Freudenstein et al 1994
- Frey 2011
- Fricker et al 1992
- Friction contact in clutch assemblies 1987
- Friddell and Franke 1990
- Friedman et al 1984
- Friedrich and Robertson 2015
- Friedrichs et al 2000
- Friend 1964
- Fritsch et al 1997
- Frohnapfel and O’Brien 2015
- Frohnapfel et al 2017
- Frohnapfel et al 2017
- Frost 1968
- Frost and Bishop 1963
- Frost and Rutherford 1963
- Frost et al 2002
- Frost et al 2009
- Frulla 2021
- Fu et al 2015
- Fuhs 1971
- Fujii et al 2020
- Fujino and Kawamura 2003
- Fujiwara et al 2026
- Fulton and Ormiston 2001
- Fulton et al 2026
- Fung 1982
- Furey 1983
- Gacherieu and Weber 1998
- Gagnon et al 1997
- Gaiddon and Knight 2003
- Gainutdinova and Gainutdinov 2018
- Gal-Or 1990
- Gal-Or et al 1993
- Galdieri et al 1992
- Gallani et al 2020
- Gallops et al 1990
- Gamon 1988
- Gan et al 2016
- Gan et al 2016
- Ganesh et al 2021
- Gao 2023
- Gao and Barber 2002
- Gao and Xu 2022
- Gao et al 2001
- Gao et al 2017
- Gao et al 2018
- Gao et al 2019
- Gao et al 2022
- Gao et al 2026
- Garabedian 1976
- Garcia et al 2009
- Garcia et al 2026
- Gardner 1999
- Gardner and Adams 1975
- Garg 1993
- Garg 1993
- Garg and Mattern 1991
- Garg and Mattern 1994
- Garg and Ouzts 1991
- Garg and Schmidt 1993
- Garg et al 1989
- Garg et al 1990
- Garg et al 1991
- Gargiulo 1986
- Garland 1987
- Garner 1967
- Gaston et al 1984
- Gates and Cochran 1961
- Gatley et al 2000
- Gatley et al 2001
- Gatley et al 2002
- Gatta et al 2018
- Gea et al 1991
- Gearhart et al 1969
- Gebril and Kamal 2023
- Geisbert and Schroeder 2008
- Gelhausen and Wilson 1986
- General Electric Co Cincinnati Oh 1962
- General Electric Co Cincinnati Oh 1963
- General Electric Co Cincinnati Oh 1964
- Gennaretti et al 2016
- Gennaretti et al 2023
- George 1999
- George et al 1964
- Gerdes 1993
- Gerdes 1993
- Gerdes and Hynes 1971
- Gerdes and Hynes 1975
- Gerken 1979
- Gern et al 2014
- Gero 2001
- Getachew and Zeleke 2024
- Ghaedrahmati and Gosselin 2022
- Ghareeb 1964
- Gibs et al 1975
- Gibson and Taccini 1989
- Gideon and Wasek 2015
- Gielow 1971
- Giesecke and Friedrichs 2019
- Gil et al 1994
- Gilbert 1985
- Giles 1944
- Gill 1973
- Gill and Lee 2025
- Gillan 1993
- Gilyard and Orme 1992
- Gilyard et al 1991
- Gingras 1999
- Ginzburg 1976
- Giri and Turner 2024
- Giri et al 2020
- Giri et al 2020
- Girshovich 1968
- Gissendanner 1981
- Giurca 2014
- Gkoutzamanis et al 2020
- Gleiter 1976
- Glezer et al 1985
- Glielmo and Vasca 2000
- Godston and Reynolds 1983
- Goeing et al 2024
- Goericke et al 2024
- Goetz et al 1976
- Goff et al 2015
- Gogoi 2021
- Goland et al 1964
- Goldberg et al 2016
- Goldberger 1966
- Gong et al 2021
- Gonzalez et al 2026
- Goparaju et al 2018
- Gorham 1977
- Gorrell et al 2001
- Gosselin et al 1998
- Goswami et al 2015
- Gotlieb 1977
- Goto et al 2021
- Goudswaard et al 2024
- Govdeli et al 2019
- Goyal 2026
- Goyal et al 2025
- Graham 1973
- Graham and Bhandari 2022
- Grahame 1968
- Grahame 1969
- Gran et al 1977
- Gratzer and Mahal 1972
- Grava et al 2026
- Gray et al 1953
- Gray et al 2017
- Gray et al 2018
- Gray et al 2018
- Gray et al 2020
- Green and Andrews 1989
- Green and Bogle 1991
- Green and Cyrus 1977
- Green and Findlay 2016
- Green and Zeckhauser 2019
- Greene 1977
- Greene 2020
- Greer 2010
- Gregory and Han 2003
- Greif et al 1972
- Griffin 1983
- Griffin 2012
- Griffin et al 2000
- Gringorten 1967
- Gringorten and Tattelman 1970
- Griswold 2000
- Groen 1988
- Grossman 1963
- Grunnet 1971
- Grunwald 1964
- Gryazev and Karabasov 2018
- Gryazev et al 2022
- Gu et al 2016
- Guajardo 2020
- Guan and Yarng 1987
- Guan et al 2025
- Gudi and Hindasageri 2021
- Guerrero et al 2003
- Guimarães et al 2018
- Guinivan 2004
- Gundy-Burlet and Kaneshige 2001
- Guner 2022
- Guner et al 2019
- Guo and Zhou 2026
- Guo et al 2015
- Guo et al 2023
- Guo et al 2023
- Gupta 1973
- Gustafson 1962
- Gutmark et al 1978
- Guttman and Crutcher 1968
- Güllü and Aran 2023
- Ha et al 2020
- Ha et al 2025
- Haas and Karanian 1980
- Habermann 2020
- Habib et al 2018
- Hagseth 1987
- Hah 2010
- Hah 2015
- Hah et al 2015
- Hahn and Wilson 1985
- Hahn and Wilson 1985
- Haibo and He 2022
- Hakim et al 2020
- Halder and Benedict 2018
- Hall 1965
- Hall 1970
- Hall and Hodder 1971
- Hall and Lieu 2021
- Hall et al 2016
- Hall et al 2017
- Hall et al 2022
- Hallez et al 2018
- Hallstaff 1966
- Halwas and Aggarwal 2019
- Halyo 1996
- Hamed et al 1997
- Han et al 2002
- Han et al 2017
- Han et al 2024
- Han et al 2026
- Handschuh 1992
- Handschuh and Bibel 1999
- Hange and Wardwell 1992
- Hange and Wardwell 1993
- Hange et al 1996
- Hange et al 1996
- Hanjie et al 2023
- Hans et al 2021
- Hansen 1965
- Hansen 2023
- Hao et al 2026
- Harding
- Hardy 1987
- Harefors and Bates 2003
- Haria et al 2018
- Hariharan et al 2015
- Hariharan et al 2017
- Harkegard 2003
- Harloff and Smith 1996
- Haro 2003
- Harradine 1977
- Harris 1984
- Harris 1999
- Harris and Lewis 2012
- Harris et al 2016
- Hart et al 2025
- Hartman et al 2025
- Hartmann et al 2016
- Hartmann et al 2017
- Hartnett and Mittlesteadt 2000
- Harun-Or-Rashid et al 2015
- Harvey and Monarch 1968
- Hasan et al 2022
- Hasegawa et al 1981
- Hasegawa et al 2018
- Hashem Dabaghian and Halder 2025
- Hashem Dabaghian et al 2025
- Hashmi and Radhakrishna 2015
- Hatta and Matsuki 1964
- Hattori and Nagano 2004
- Haug and Niehuis 2018
- Havey and Kline 1989
- Haviland and Herling 1977
- Hawkins 1974
- Hawkins 1980
- Hayami et al 2002
- Hayase 1974
- Hayes and Caverly 2020
- Hazen and Seckel 1950
- He 2024
- He and Liu 2018
- He and Liu 2023
- He et al 2013
- He et al 2018
- He et al 2020
- He et al 2024
- He et al 2024
- He et al 2026
- He et al 2026
- He-yun et al 2021
- Heath et al 2017
- Hebbar et al 1999
- Hebert et al 1970
- Hebert et al 1973
- Hegarty et al 1965
- Hegde 2020
- Hegde et al 2019
- Heimerl and Benedict 2022
- Hein and Myschik 2022
- Heinlein et al 2020
- Heinlein et al 2024
- Heiran et al 2017
- Helicopter and V/Stol Aircraft
- Henderson 1964
- Henderson and Lavretsky 1999
- Henderson and Walters 1981
- Herbst 1980
- Herbst and Ross 1970
- Herbst et al 2015
- Hermes and Wood 1969
- Hernández et al 2003
- Herrick 1986
- Herrick 1988
- Herrick 1989
- Hertz and Hughes 1998
- Herzog et al 2021
- Herzog et al 2024
- Hess 1977
- Hess 1988
- Hess et al 2026
- Heyson 1973
- Heyson and Katzoff 1956
- Heyson and Katzoff 1957
- Hicks et al 2023
- Hienz and Vedova 1984
- Hiers 2018
- Hiers et al 2004
- Highly elastic carbon fiber reinforced plastic propulsion shaft 1996
- Hile and Denny 1954
- Hiley and Bowers 1981
- Hill 1966
- Hill 1970
- Hill 1975
- Hill 1981
- Hill 1987
- Hill 1993
- Hill and Jenkins 1979
- Hill and Waters 1974
- Hillaker 1983
- Hiller Aircraft Corp Palo Alto Ca 1965
- Hiller Aircraft Corp Palo Alto Ca 1965
- Hiller Aircraft Corp Palo Alto Ca 1965
- Hiller Aircraft Corp Palo Alto Ca 1965
- Hiller Aircraft Corp Palo Alto Ca 1965
- Hinchliffe and Qin 2016
- Hindson and Hardy 1980
- Hindson et al 1982
- Hindson et al 1993
- Hinz and Miller 1979
- Hirano et al 2019
- Hirschkron et al 1979
- Hirsh 1965
- Hirt et al 2017
- Hiyama 1974
- Ho et al 2019
- Hodges et al 1988
- Hoffman 1971
- Hoffman and Allman 1978
- Hoffman et al 2017
- Hoffman et al 2018
- Hoh and Mitchell 1983
- Hoh et al 1981
- Holdaway 1954
- Holgerson 1997
- Holgerson 1999
- Holgerson 2000
- Holgerson and Lundberg 1999
- Hollingsworth et al 1977
- Holzhauser et al 1972
- Homans et al 1978
- Hong and Jeon 1994
- Hong and Lee 2002
- Hong et al 2025
- Hong et al 2025
- Hongo and Tanaka 1973
- Hooker 1981
- Horn et al 2014
- Horne and Leland 1962
- Horowitz et al 2016
- Horvath 2019
- Horvath and Wells 2018
- Hoskin 1993
- Hoskin et al 1991
- Hosotani et al 2019
- Hot gas ingestion and the speed needed to avoid ingestion for transport type STO/VL and STOL configurations 1984
- Hou et al 2021
- Hou et al 2024
- Houjoh et al 2015
- Houx et al 2022
- Howard and Gallimore 1992
- Howard and Puterbaugh 2016
- Howard et al 2017
- Howe and McKibbin 1989
- Howell and Korst 1971
- Howerton and Slater 2021
- Hozumi and Aihara 2018
- Hromisin et al 2015
- Hsiao et al 2004
- Hsin 1974
- Hsu et al 2023
- Hsu et al 2025
- Hu and Booker 2022
- Hu and Christopher 2018
- Hu et al 2016
- Hu et al 2019
- Hu et al 2024
- Hu et al 2024
- Hu et al 2026
- Hua et al 2025
- Huan et al 2021
- Huang 2023
- Huang and Macinnes 1988
- Huang et al 1999
- Huang et al 2015
- Huang et al 2020
- Huang et al 2020
- Huang et al 2022
- Huang et al 2022
- Huang et al 2024
- Huang et al 2024
- Huang et al 2025
- Huang et al 2025
- Huang et al 2026
- Huber et al 1993
- Hudson 1977
- Hudson and Gee 1977
- Huete and Singh 1997
- Huggett 1959
- Hughes 2017
- Hughes et al 2002
- Hughes Tool Co Culver City Ca 1963
- Huh et al 2015
- Humbert et al 2021
- Humphreys et al 1988
- Hung and Lin 1994
- Hunt and Gowadia 1981
- Hunt et al 1977
- Hunter and Cawthon 1984
- Hunter and Cawthon 1985
- Hunter et al 2002
- Huntley 1972
- Hutcheson 1976
- Hutchison et al 1983
- Hwang 1988
- Hwang 1990
- Hwang and Tsou 1981
- Hwang et al 2023
- Hyde and Glover 1991
- Hynes et al 1989
- Hyun 1996
- Hyun et al 2023
- Ichikawa and Watanabe 1995
- Ichikawa and Watanabe 1996
- Ichikawa et al 2020
- Idzorek 1988
- Ilyas et al 2023
- Imani and Anjomrouz 2025
- Imfeld 1974
- Imhof and Schork 1999
- Imlay 1986
- Incorporating agility flight test metrics concurrently into the aircraft preliminary design process 1994
- INFORMATION MODEL OF AIRCRAFT WEIGHT PROFILE 2021
- Ing and Zhang 1993
- Ing and Zhang 1994
- Ing et al 2002
- Ingraham and Falck 2025
- Innocenti 1999
- Integrated flight/propulsion control - Methodology, design, and evaluation 1985
- Integration and simulated flight 1977
- Invernizzi et al 2018
- Investigation on the inflow distortion of a propulsive fuselage aircraft and its impact on the propulsion fan performance 2023
- Iqbal et al 2015
- Irvin and Swan 1956
- Iseni et al 2016
- Ishutinov et al 2024
- Isidori et al 2001
- Isikveren 2018
- Islam and Islam 2017
- Islam et al 2018
- Islam et al 2018
- Isomura and Giles 1998
- Ison 2024
- Issa et al 2016
- Issac et al 2019
- Ito et al 2018
- Ivler and Geyer 2024
- Iwasa et al 2018
- Iwatsubo et al 1984
- Iyer and Takahashi 2024
- Jabbar et al 2021
- Jabbar et al 2023
- Jackson 1965
- Jackson 1970
- Jackson and House 1982
- Jacobellis and Gandhi 2016
- Jacobson and Smith 2018
- Jacuzzi and Granlund 2019
- Jafari et al 2022
- Jain 2017
- Jain 2018
- Jain 2018
- Jakobsson 1951
- Jalabert and Bellan 2024
- Jambunathan et al 1992
- Jammalamadaka et al 2020
- Jang 2015
- Jang 2022
- Jang et al 2012
- Jang et al 2022
- Janon 2020
- Jansen et al 2017
- Jansen et al 2019
- Jasudavisius 2021
- Jaw and Garg 2005
- Jayasundara and Baeder 2023
- Jenista and Sheridan 1987
- Jenkins and Marks 1975
- Jente 2022
- Jeong and Cho 2026
- Jeong et al 2019
- Jeong et al 2024
- Jeong et al 2026
- Jesudasan et al 2026
- Jewell et al 1979
- Ji and Xie 2023
- Jia and Lee 2020
- Jia and Lee 2021
- Jia et al 2018
- Jia et al 2024
- Jia et al 2025
- jian-jian et al 2019
- Jiang and Behbahani 2020
- Jiang and Pakmehr 2022
- Jiang and Zhang 2016
- Jiang and Zhang 2016
- Jiang and Zhang 2017
- Jiang and Zhang 2018
- Jiang and Zhang 2021
- Jiang et al 2015
- Jiang et al 2015
- Jiang et al 2018
- Jiang et al 2022
- Jiang et al 2023
- Jiang et al 2023
- Jiang et al 2025
- Jimenez 2001
- Jimenez et al 2016
- Jimenez Garcia and Barakos 2018
- Jimenez-Garcia et al 2017
- Jin and Zhao 2025
- Jin et al 2020
- Jin et al 2023
- Jinxin et al 2026
- Jo and Kwon 2019
- Jo et al 2017
- Johansen 2016
- John et al 2018
- Johns 1989
- Johns 1998
- Johns et al 1988
- Johns et al 1989
- Johns et al 1989
- Johns et al 1990
- Johns et al 1990
- Johnson 1972
- Johnson 1985
- Johnson 1990
- Johnson 1991
- Johnson 2003
- Johnson and Craig 1974
- Johnson and Silva 2026
- Johnson and Sirohi 2024
- Johnson et al 2007
- Johnson et al 2024
- Johnson et al 2024
- Johnston 1965
- Johnston and Fleeter 2004
- Johnston and Friend 1965
- Johnston et al 1965
- Jois et al 2024
- Jones 1960
- Jones 1966
- Jones 1975
- Jones 2014
- Joo 2000
- Joppa 1969
- Jordan 1974
- Joseph and Badrya 2026
- Joshi and Compton 1985
- Joshi et al 2024
- Jun et al 2018
- Jung et al 2026
- Jung et al 2026
- Juvé et al 2016
- Jyothy and John Wessley 2023
- Kabaliswaran and Das 2026
- Kabra 2022
- Kadhim et al 2020
- Kadhiresan and Duffy 2019
- Kaemming and Smith 1984
- Kaewbumrung and Plengsa-Ard 2023
- Kaewchoothong 2025
- Kai 2024
- Kakavitsas et al 2024
- Kalemaris and Cea 1977
- Kamada et al 2019
- Kamal and Livesey 1979
- Kaman Aircraft Corp Bloomfield Ct 1964
- Kamath et al 2025
- Kamman and Hall 1978
- Kamman and Perryman 1982
- Kamman et al 1979
- Kandath et al 2019
- Kandel et al 2022
- Kanemitsu 1985
- Kanemoto et al 2002
- Kaneshige et al 2023
- Kang 2022
- Kang and Kwon 2001
- Kang et al 2017
- Kang et al 2021
- Kang et al 2023
- Kang et al 2025
- Kang et al 2025
- Kanistras et al 2016
- Kannan et al 2025
- Kansas Univ Lawrence 1952
- Kansas Univ Lawrence 1952
- Kantner et al
- Kappus 1969
- Kapstein 2004
- Kara and Kurtuluş 2024
- Kara-Mohamed et al 2023
- Karamoozian et al 2018
- Karemaa 1971
- Kashimura et al 1999
- Katagiri et al 2025
- Kataoka et al 1982
- Kataria 2022
- Kato and Yamane 1979
- Kato et al 1981
- Katoh et al 1998
- Katz 1988
- Kaushik et al 2025
- Kawachi 1982
- Kawasaki 1965
- Kaya 1998
- Kazan and Krause 1967
- Kazan and Krause 1968
- Keeler 2005
- Kefayat and Kamali 2024
- Keller 1969
- Keller 1982
- Keller 2021
- Keller 2023
- Keller 2025
- Keller et al 2018
- Keller et al 2024
- Kelley et al 1982
- Kelley et al 2021
- Kennedy and Stuart 2025
- Kentfield 1967
- Kentfield 1975
- Kenyon 1974
- Kerho 2015
- Kern and Hopcroft 1983
- Kerr and Bensmiller 2024
- Key 1971
- Keye et al 2017
- Keye et al 2023
- Keçeci et al 2025
- Khader 1971
- Khader and Loewy 1989
- Khalaji et al 2015
- Khaleghi and Jalaly 2016
- Khaletskii et al 2024
- Khalid 1989
- Khalid 1992
- Khan et al 2025
- Khanh Tran 2020
- Khlebnikov 1990
- Khobragade et al 2021
- Kidd 1966
- Kidwell 1963
- Kidwell 1981
- Kidwell and Lampkin 1983
- Kidwell and Rapp 1985
- Kilner 1982
- Kim 2016
- Kim 2026
- Kim and Choi 2024
- Kim and Jo 2025
- Kim and Kim 2001
- Kim and Kwon 2015
- Kim and Lee 2021
- Kim and Park 2001
- Kim and Park 2003
- Kim and Park 2025
- Kim and Stern 1990
- Kim and You 2026
- Kim et al 2001
- Kim et al 2008
- Kim et al 2016
- Kim et al 2018
- Kim et al 2018
- Kim et al 2020
- Kim et al 2020
- Kim et al 2025
- Kimberlin 1987
- Kimura et al 2022
- Kimura et al 2023
- Kinematic Analysis of RSSR spatial mechanism, A Review 2017
- King 1961
- King and Schnelker 1970
- King et al 1991
- Kinzer 2008
- Kinzie et al 1998
- Kirk and Barrack 1969
- Kirk et al 1972
- Kirner et al 2015
- Kitaplioglu 1986
- Kitaplioglu and Kinney 1986
- Kitchenside 1958
- Kitowski 1986
- Kitowski 1992
- Klann et al 1984
- Klausmeyer 2004
- Kleckner 1973
- Klestov 1978
- Klimchenko et al 2023
- Klinar and Craig 1961
- Klingloff et al 1965
- Klunk and Freeman 2018
- Knight et al 1973
- Knoerzer et al 2018
- Knott 1974
- Knott 1977
- Knott 1987
- Knox 1962
- Knox and Meyer 1984
- Kochanski 1966
- Kodama and Namba 1992
- Koenig et al 1977
- Kofman and Becus 1996
- Kohl and Algranti 1957
- Kohn 1972
- Kohn 1979
- Kohn 1983
- Kohout 2003
- Kohout 2004
- Kohout and Schmitz 2003
- Kolesar et al 2019
- Komerath et al 1985
- Komerath et al 1988
- Koncsek 1981
- Koncsek and Syberg 1977
- Kondo et al 2003
- Kong 2015
- Kong 2016
- Kong 2016
- Kong et al 2004
- Konyukov 2025
- Konyukov 2026
- Kopaç 2002
- Koratkar and Chopra 2001
- Korsun et al 2017
- Korzun 1976
- Kos et al 1973
- Koshel et al 2026
- Kosir et al 2020
- Kostenko and Tolstonogov 2021
- Kotansky 1978
- Kotansky 1982
- Kotansky and Glaze 1981
- Kotaru et al 2019
- Kotidis and Epstein 1990
- Kou et al 2021
- Kovach and Sandercock 1961
- Kovich and Moore 1976
- Kovich and Steinke 1976
- Kovich et al 1977
- Kowalski et al 2021
- Kozak et al 2019
- Kozakiewicz and Grzegorczyk 2021
- Kozapalli and Warmbrodt 1997
- Kozlak et al 2017
- Krahnstoever et al 2026
- Kramer and Hall 2025
- Kramer et al 2024
- Krammer and Holzapfel 2023
- Kranenburg et al 1986
- Krasheninnikov et al 1996
- Krasnow 1985
- Krenkel and Salzman 1968
- Krepski and Hudson 1981
- Krimphove et al 2023
- Krishna and Vancoillie 1999
- Krishna et al 1994
- Krishnamoorthy 1971
- Kristy 1995
- Krivec et al 1984
- Krosche and Heinze 2015
- Krothapalli 1983
- Krothapalli et al 1985
- Krothapalli et al 2003
- Krouse et al 2022
- Krueger and Minzner 1976
- Kruger and Uranga 2020
- Kruger and Uranga 2024
- Ku and Sankar 2026
- Kuang and Zhu 2015
- Kuchinka 1966
- Kucuk 2017
- Kuenkler 1982
- Kuhlman and Warcup 1977
- Kuhlman and Warcup 1978
- Kuhlman and Warcup 1979
- Kuhlman and Warcup 1980
- Kuhn 1979
- Kuhn 1980
- Kuhn 1981
- Kuhn and McKinney 1965
- Kuhn et al 1979
- Kuhn et al 1993
- Kuhn et al 1993
- Kulhánek et al 2023
- Kumada and Mabuchi 1970
- Kumar et al 1998
- Kumar et al 2018
- Kumar et al 2020
- Kumar et al 2021
- Kumar et al 2023
- Kumon et al 2010
- Kuntz 1996
- Kuntz et al 1997
- Kunwar and Chakraborty 2025
- Kurosaka 1984
- Kurt 2024
- Kurt 2026
- Kurtz 1976
- Kurushin et al 2018
- Kurylowich and Ritter 1970
- Kusunose et al 2000
- Kutney 1963
- Kutney 1964
- Kutney and Piszkin 1963
- Kuzmin 2021
- Kuznetsov et al 1985
- Kuzniar et al 2020
- Kwon and Sankar 1991
- Kwon and Sankar 1992
- König and Fares 2018
- L’Ecuyer et al 1971
- Lacey and Miller 1977
- Lacey et al 1979
- Lai and Le Tri 2017
- Laitone 1981
- Lak et al 2020
- Lake 1990
- Lake et al 2000
- Lakshminarayana and Popovski 1986
- Lam 1998
- Lamar 2004
- Lambregts 1983
- Lammen et al 2025
- Lampl and Armanini 2023
- Lampl and Hornung 2018
- Lamprakis et al 2025
- Lan et al 2025
- Lancey and Cooper 1989
- Land and Clark 1965
- Landgrebe 1971
- Landry 2005
- Landy and Kim 1984
- Lang et al 2024
- Large 1981
- Larson and Schweikhard 1974
- Lashkov and Shumilkina 1982
- Laskaridis 2015
- Laudeman 1972
- Lavi 1966
- Lavi 1967
- Le Chuiton 2004
- Leal Junior et al 2016
- Lebacqz and Radford 1978
- Lebacqz and Radford 1979
- Lechniak et al 2020
- Lecuyer 1970
- Lee and Boedicker 1985
- Lee and Dassonville 2019
- Lee and Franz 1976
- Lee and Kim 1993
- Lee and Park 2022
- Lee and Yan 1992
- Lee and Yee 2016
- Lee and Yee 2024
- Lee et al 1973
- Lee et al 1988
- Lee et al 2003
- Lee et al 2004
- Lee et al 2016
- Lee et al 2018
- Lee et al 2019
- Lee et al 2021
- Lee et al 2022
- Lee et al 2023
- Lee et al 2024
- Lee et al 2026
- Lee-Rausch et al 2004
- Leese 1964
- Leese 1966
- Leese 1972
- Leese and Knight 1974
- Legrand et al 2024
- Legrand et al 2025
- Lehman 1964
- Lehtinen and Zeller 1972
- Lei and Zha 2022
- Lei and Zhao 2023
- Leib et al 2017
- Leitner 1986
- Lemanov et al 2018
- Lemelin et al 2026
- Lengyel-Kampmann et al 2024
- Lengyel-Kampmann et al 2024
- Lents 2021
- Leovan 2019
- Lepicovsky and Bell 1983
- Lesieutre and Sullivan 1986
- Levin and Wardwell 1997
- Levin et al 2018
- Levine and Inglis 1989
- Levinsky and Ramsey 1972
- Levinsky et al 1968
- Levinsky et al 1969
- Levinsky et al 1970
- Lewis 1989
- Lewis 2000
- Lewis 2002
- Lewis and Hurd 1980
- Lewis and Lewis 1981
- Lewis and Moore 1976
- Lewis and Simpkin 1981
- Li 2008
- Li and Li 2024
- Li and Liu 2023
- Li and Wells 1999
- Li and Wu 2024
- Li and Xia 2018
- Li and Yu 2001
- Li et al 2002
- Li et al 2016
- Li et al 2016
- Li et al 2016
- Li et al 2016
- Li et al 2016
- Li et al 2017
- Li et al 2017
- Li et al 2017
- Li et al 2018
- Li et al 2019
- Li et al 2020
- Li et al 2020
- Li et al 2020
- Li et al 2020
- Li et al 2021
- Li et al 2021
- Li et al 2021
- Li et al 2022
- Li et al 2022
- Li et al 2022
- Li et al 2022
- Li et al 2022
- Li et al 2023
- Li et al 2023
- Li et al 2023
- Li et al 2023
- Li et al 2024
- Li et al 2024
- Li et al 2024
- Li et al 2024
- Li et al 2024
- Li et al 2025
- Li et al 2025
- Li et al 2025
- Li et al 2025
- Li et al 2026
- Li et al 2026
- Liang 1989
- Liang and Fu 1991
- Liang and Yeuan 1997
- Liang et al 2023
- Liang et al 2024
- Liao and Bang 2023
- Liao et al 2024
- Liao et al 2024
- Liao et al 2025
- Libraschi et al 2023
- Libório et al 2025
- Licata and Burcham 1983
- Lichota 2023
- Lichtsinder et al 1998
- Lidor et al 2019
- Lieblein 1970
- Lieblein et al 1973
- Lieder et al 2025
- Lieu 1964
- Lift Loss In Hover 2007
- Lim and Chjng 1989
- Lim and Jung 2025
- Lim and Yee 2026
- Lim et al 2026
- Lima et al 2019
- Lin et al 2018
- Lin et al 2019
- Lin et al 2019
- Lind and Tamplin 1981
- Lindblad et al 2018
- Linderman et al 1974
- Lindner et al 2023
- Linnell 1963
- Lipera and Sandlin 1984
- Lissaman 1967
- Lissaman 1968
- Lissaman 1969
- Lissaman 1969
- Liston and Small 1992
- Litt 2026
- Litt et al 2026
- Liu 2002
- Liu 2023
- Liu and Mi 2025
- Liu and Tan 2024
- Liu and Vo 2024
- Liu and Wang 2024
- Liu and Wu 2023
- Liu and Zhang 2024
- Liu and Zhao 2019
- Liu et al 2004
- Liu et al 2015
- Liu et al 2017
- Liu et al 2018
- Liu et al 2018
- Liu et al 2019
- Liu et al 2020
- Liu et al 2021
- Liu et al 2021
- Liu et al 2022
- Liu et al 2022
- Liu et al 2022
- Liu et al 2022
- Liu et al 2022
- Liu et al 2023
- Liu et al 2023
- Liu et al 2023
- Liu et al 2023
- Liu et al 2023
- Liu et al 2023
- Liu et al 2023
- Liu et al 2024
- Liu et al 2024
- Liu et al 2024
- Liu et al 2024
- Liu et al 2025
- Liu et al 2025
- Liu et al 2025
- Liu et al 2025
- Liu et al 2025
- Liu et al 2025
- Liu et al 2025
- Liu et al 2026
- Liu et al 2026
- Liu et al 2026
- Liu et al 2026
- Liuqing Yang et al 2016
- Lobo et al 2016
- Lockwood 1963
- Lollar and Matous 1963
- Lollar et al 1965
- Long 1993
- Long et al 2026
- Longxin 2025
- Lopez and Shen 1971
- Lopez et al 1979
- Lord 1985
- Lorell 1989
- Loth and McCormick 1986
- Loth et al 1974
- Loth et al 1976
- Lou et al 2003
- Lou et al 2024
- Louthan 1980
- Love 1993
- Love 2022
- Lowe and Sanger 1972
- Lowenberg and Jones 2003
- Lozano et al 2022
- Lu and Jain 1998
- Lu and Terrier 2003
- Lu and Terrier 2003
- Lu et al 2017
- Lu et al 2018
- Lu et al 2019
- Lu et al 2019
- Lu et al 2019
- Lu et al 2022
- Lu et al 2022
- Lu et al 2022
- Lucas 1978
- Luce 1949
- Luidens et al 1984
- Lund et al 1986
- Luo et al 2018
- Luo et al 2020
- Luo et al 2023
- Luo et al 2024
- Luo et al 2025
- Luo et al 2026
- Lv et al 2016
- Lyga 1990
- Lykyanov and Adler 2023
- Lympany and Page 2024
- Lynch 1972
- López de Vega et al 2019
- López de Vega et al 2021
- Lück et al 2025
- Lück et al 2026
- Ma
- Ma et al 2016
- Ma et al 2016
- Ma et al 2017
- Ma et al 2017
- Ma et al 2018
- Ma et al 2020
- Ma et al 2022
- Ma et al 2024
- Maadani et al 2023
- Mace and Doane 1990
- Mace and Nyberg 1992
- Macha 1977
- Machado et al 2025
- Macit and Özer 2025
- Mack 1965
- Mackintosh and Dawson 1979
- Maclean 1991
- Maddock et al 2011
- Madeiras et al 2026
- Madelung 1977
- Maekawa et al 1978
- Magata et al 2025
- Magliozzi 1987
- Magrini 2022
- Magrini and Benini 2026
- Magrini et al 2023
- Mahlmeister et al 1955
- Mahmud et al 2018
- Mahmuddin 2017
- Mahna and Asnani 1989
- Mahvelatishamsabadi and Emadi 2020
- Maiden and Petit 1975
- Maisel and Harris 1981
- Maita et al 1983
- Maita et al 1990
- Majka and Muszyńska-Pałys 2023
- Mak et al 2023
- Makarov 2019
- Malaek and Parastari 2001
- Malaek and Soltan-Mohammed 2001
- Malan and Brown 1994
- Maldonado and Fernandes 2024
- Maldonado et al 2024
- Malick and Agarwal 2015
- Malmuth et al 1986
- Malpica et al 2024
- Mandal et al 2020
- Mandeles 1998
- Mange et al 2002
- Manley and von Klein 2002
- Mann and Mercer 1986
- Manoilo 2025
- Mansell 1987
- Mansouri et al 2000
- Manzoor et al 2020
- Mao et al 2022
- Marchese 1963
- Marconi et al 2002
- Marepally et al 2025
- Margason 1966
- Margason 1970
- Margason 2002
- Margason 2002
- Margason and Hoad 1979
- Margason and Kuhn 1988
- Margason and Tso 1993
- Margason et al 1996
- Marien et al 2018
- Mark 1987
- Marksel and Prapotnik Brdnik 2022
- Marques Goncalves et al 2024
- Marsh 1961
- Marter et al 2020
- Martin 1964
- Martin 2025
- Martin et al 1999
- Martindale et al 1974
- Martinez et al 2025
- Martinez Rodriguez and Blaesser 2024
- Martins and Guenther 2003
- Martinsson and Liu 2016
- Martínez Fernández and Smith 2020
- Marvin 1968
- Mason 1982
- Mason 1990
- Massardo and Satta 1987
- Masson et al 1998
- Masson et al 1999
- Matamoros and de Visser 2018
- Matesanz et al 1995
- Matesanz-García et al 2022
- Mathews 1987
- Mathews and Rothstein 1998
- Mathioudakis 1985
- Mathur 1998
- Mathur and Atkins 2025
- Mathur and Atkins 2026
- Matous et al 2021
- Mattern and Garg 1992
- Mattern et al 1989
- Mattiazzo et al 2002
- Mattingly 1989
- Matwey et al 1983
- Maurel and Solliec 2001
- Maurya et al 2021
- Maurya et al 2023
- Mavriplis and Levy 2002
- May and Widdison 1971
- May et al 2022
- May et al 2023
- May et al 2024
- May et al 2024
- May et al 2025
- May et al 2026
- Mayda et al 2024
- Mayer and Paynter 1994
- Mays 1969
- McAmis and Bartlett 1991
- McArdle and Esker 1993
- McArdle and Smith 1990
- McCallum 1989
- McCarthy 1992
- McCarthy 2002
- McCarthy and Kelly 1993
- McConnell 2006
- McCormick 1969
- McCormick and Surko 1989
- McCown 2011
- McCrink and Gregory 2015
- McCrink and Gregory 2017
- McCune 1993
- McDonald 2015
- McDonald 2016
- McDonnell Aircraft Corp St Louis Mo 1950
- McGuigan 1970
- McGuirk et al 2002
- McIntyre 1963
- McKinney and Kirby 1964
- McLafferty and Peterson 1983
- McMurray et al 2019
- McNally 1986
- McNally and Bach 1988
- McNeill et al 1995
- McNicol 2014
- McNicol 2014
- McNicol and Wu 2014
- McRuer 1991
- McVey et al 1969
- Meakin 1995
- Mechanisms of transonic blade-vortex interaction noise 1976
- Meckstroth and Blake 2015
- Meckstroth and Ordóñez 2020
- Medd et al 2003
- Megat et al 2026
- Mehalic and Lottig 1987
- Mehta et al 2015
- Meiklem 1969
- Mele et al 2017
- Melo et al 2026
- Mendenhall and Spangler 1976
- Mendenhall et al 1972
- Menegozzo and Benini 2020
- Menegozzo and Benini 2020
- Meng and Lu 1993
- Meng et al 2015
- Meng et al 2026
- Mennicken et al 2019
- Meola et al 1995
- Merchant 1949
- Merchant et al 2003
- Merchant et al 2004
- Merewether 1963
- Merrick 1981
- Merrick 1982
- Merrick 1984
- Merrick et al 1991
- Mertens et al 1986
- Meyer et al 1991
- Meyer et al 2024
- Meyn et al 1993
- Mezzacapo et al 2025
- Mi 2020
- Miao et al 2015
- Michaels 1969
- Michaelsen 1971
- Michalík and Čerňan 2020
- Michaud et al 2016
- Micklos 1991
- Middleton and Srivatsan 1987
- Middleton et al 1988
- Middleton et al 1992
- Mieloszyk and Tarnowski 2019
- Migbee et al 1987
- Mihalik and Keane 2022
- Mihaloew 1981
- Mihaloew and Drummond 1989
- Mihaloew and Roth 1982
- Mihaloew and Weiss 1989
- Mihaloew et al 1981
- Mihaloew et al 1988
- Mihaloew et al 1988
- Mikhail 1979
- Miles 1953
- Miles 1954
- Miller 1973
- Miller 1983
- Miller 1995
- Miller and Koch 1985
- Miller and Papamoschou 2024
- Miller and Protopapas 1985
- Miller et al 1981
- Miller et al 1991
- Miller et al 2023
- Milligan et al 1994
- Milligan et al 1995
- Min et al 2018
- Min et al 2026
- Minardi 1982
- Minervino et al 2022
- Mirza-Baig and Saravanamuttoo 1991
- Misiorowski et al 2019
- Misiorowski et al 2019
- Mitchell et al 1992
- Miwa and Marubashi 2014
- Mixson et al 1975
- Miyazaki and Tsubakino 2017
- Mo et al 2024
- Modeling and Data Fusion 2021
- MODELLING AND CONTROLLER DESIGN OF A NOVEL DUCTED FAN UNMANNED AIRCRAFT 2021
- Moellmann and O’Connor 1967
- Moger and Ramsay 1964
- Mohammadi et al 2023
- Mohire et al 2018
- Mohire et al 2019
- Moin and Lele 1998
- Moirou and Sanders 2026
- Moirou et al 2023
- Moller 1985
- Moller 1998
- Molyneux 1983
- Momiyama 1977
- Momiyama 1977
- Montero Villar et al 2018
- Moore 1986
- Moore 2010
- Moore and Collins 1937
- Moore and Ning 2019
- Moore and Reid 1972
- Moore and Reid 1982
- Moore et al 1978
- Moore et al 1979
- Moore et al 2013
- Moore et al 2026
- Moorhouse 1990
- Moralez et al 1987
- Morani et al 2024
- More and Datta 2003
- Moreau et al 2024
- Morelli 2021
- Morra and Nicolosi 2025
- Morse and Newhouse 1960
- Morse and Newhouse 1961
- Morse and Newhouse 1961
- Mortimer et al 2023
- Morton 1983
- Moss 1995
- Motycka 1985
- Moumen Idres and Muhamad Adi Muqri Saiful Azmi 2022
- Mount 1964
- Mourtos et al 1995
- Moustafa et al 2025
- Mouton 2021
- Mrusek 2021
- Mruthyunjaya and Raghavan 1984
- Muehter 1974
- Mueller et al 2016
- Mufti et al 2019
- Mukherjee et al 2023
- Muller and Gasko 1967
- Muller and Wesshaar 1994
- Multimode Clutch 2018
- Mumasha et al 2026
- Murai et al 1984
- Murakoshi 1969
- Murata et al 2025
- Murata et al 2025
- Murman and Cole 1974
- Murman et al 2001
- Murphy 1957
- Murphy and Landman 2015
- Murphy and Lewis 1979
- Muscarello et al 2017
- Musgrave and Plehn 1987
- Myers 1984
- Myers et al 2010
- Myers et al 2019
- Mysko et al 1993
- Myszko and Knowles 1994
- Müller et al 1996
- Mütschard et al 2021
- Nafi and Hasan 2019
- Nag et al 2017
- Nagai et al 1996
- Nagaya et al 1982
- Nagel and Patrick 1988
- Nagler 2026
- Naida and Fonarev 1995
- Naida and Fonarev 1996
- Naik and Chiarelli 1988
- Nakaguchi 1967
- Nakamura 1988
- Nakka and Alexander-Ramos 2021
- Nakod et al 2025
- Naldi and Marconi 2009
- Naldi and Marconi 2011
- Naldi and Marconi 2013
- Nallasamy 1993
- Nallasamy et al 1988
- Nalls and Stortz 1993
- Namba 2001
- Nangia 2011
- Nango and Shizu 2001
- Nango et al 2001
- Narayanan 2003
- Nardi et al 1999
- NASA Conference on V/STOL 1960
- Natarajan and Venkatakrishnan 2019
- Natsumeda and Miyoshi 1994
- Naumowicz and Smith 1992
- Naumowicz et al 1996
- Naumowicz et al 1998
- Naval Air Test Center Patuxent River Md 1957
- Nayebi and Taeibi Rahni 2024
- Nebesar 1932
- Nederlof et al 2023
- Neighbors and Rock 1993
- Neighbors and Rock 1994
- Nelms 1978
- Nelms 1984
- Nelms and Anderson 1984
- Nelson 1986
- Neogi et al 2025
- Nery et al 2024
- Neuhoff 1985
- Newberry 1998
- Newcomb and Merritt 1962
- Newell and Herrick 1979
- Newman 1988
- Ng and Datta 2018
- Ng and Datta 2019
- Nghiem and Norstrud 1989
- Nguyen 2026
- Nguyen and Webb 2025
- Nguyen and Xiong 2026
- Nguyen et al 2018
- Nguyen et al 2023
- Nguyen et al 2025
- Ni and Lee 2025
- Ni et al 2026
- Nibin et al 2024
- Nicholas et al 1984
- Nichols and Englar 1980
- Nichols et al 2025
- Nicholson 1985
- Nicholson and Moore 1986
- Nicolay et al 2021
- Nicolosi et al 2022
- Nie 2003
- Niewald and Parker 2000
- Nigam et al 2015
- Nishikawa and Rinoie 2024
- Nishimura 1980
- Nishimura et al 2023
- Nisi and Tang 2025
- Nithya and Rashmi 2019
- Nocoń et al 2023
- Nonweiler 1956
- Nordquist et al 1972
- Norledge 1998
- Norman et al 2018
- North et al 2021
- Norton et al 1979
- Norum 1989
- Nosseir and Ho 1980
- Nosseir and Peled 1986
- Nosseir et al 1987
- Nouri Rahmat Abadi et al 2019
- Novak 1975
- Numbers and Hamed 2003
- Numerical Investigation Of Three Dimensional Laminar Jet Impingement On Heated Plate Surface 2016
- Nunez Garcia et al 2026
- Nurahmi and Gan 2018
- Nusrath et al 2016
- O’Brien 1945
- O’Brien and Datta 2026
- O’Brien and Delgado 2024
- O’Brien and Lowe 2015
- O’Bryan 1961
- O’Keefe et al 1973
- O’Rourke and Rutherford 1991
- Obikane 1984
- Obrien 1976
- Obrien 1976
- Obrien and Cramer 1986
- Obye and Hakim 1984
- Ochi and Kanai 2001
- Ockier and Celi 1991
- Odukoya and Jo 2026
- Oetting 1974
- Oganyan and Loginov 2025
- Oh 1999
- Oh and Oh 2000
- Oh et al 2024
- Okai et al 2015
- Okai et al 2020
- Oki et al 2000
- Oki et al 2002
- Okumoto and Elsanker 1973
- Okuno and Kawachi 1993
- Okuno and Kawachi 1993
- Oldeweme et al 2024
- Oliinyk and Zylevich 2026
- Oliva and Morris 2022
- Olson and Henricks 2018
- Omar and Lampkin 1977
- Onaka et al 2018
- Oole 1993
- Opalski and Sajben 2002
- Operational Aspects of the 1969
- Oravský 1999
- Orefice et al 2019
- Orefice et al 2020
- Orhan and Subbarao 2021
- Orme and Sims 1998
- Orme et al 1998
- Orme et al 2020
- Ornelas 1985
- Ornob et al 2025
- Orrick 2024
- Orzelowski and Wicher 2000
- Osborn and Hager 1976
- Osborn and Steinke 1974
- Osborn et al 1973
- Osman and Segev 1972
- Osman et al 1991
- Osman et al 2026
- Ostheimer and Giguere 1963
- Oswald et al 2004
- Otani 2023
- Ou and Tsai 1993
- Ouellette 2025
- Oumlik and Dai 2026
- Oved and Haustein 2023
- Oved et al 2024
- Overall 1976
- Overfield and Crawford 1967
- Overmeyer and Martin 2017
- Overmeyer and Martin 2017
- Owens et al 2004
- Oğur et al 2024
- Padmanabhan et al 2023
- Padthe et al 2022
- Page and Steinberg 1999
- Page et al 2017
- Page et al 2025
- Pakmehr et al 2017
- Palko 1975
- Palmer and Holdo̸ 2002
- Palmer and Waterman 1994
- Pamadi 1980
- Pandya and Uranga 2013
- Pang et al 2024
- Panish and Bacic 2025
- Papadales and Basil S. 1979
- Papamoschou 1994
- Papamoschou 1996
- Papamoschou 2023
- Pardowitz et al 2015
- Park 2025
- Park and Choi 2020
- Park and Sung 2001
- Park et al 2013
- Park et al 2015
- Park et al 2017
- Park et al 2019
- Park et al 2024
- Park et al 2025
- Park et al 2025
- Park et al 2025
- Park et al 2026
- Park et al 2026
- Parkala and Kandath 2026
- Parker 1986
- Parker 1991
- Parker and Simonson 1982
- Parker and Simonson 1982
- Parker and Simonson 1982
- Paroubek and Kynčl 1998
- Parrish 1978
- Parzych 1990
- Parzych and Shattuck 1986
- Pascioni et al 2024
- Pascioni et al 2026
- Passe et al 2015
- Pasupula and Mistry 2023
- Patierno and Asdurian 1965
- Patil and Datta 2024
- Patnaik et al 2001
- Pauli et al 1970
- Paulson 1980
- Paulson 1981
- Paulson et al 1988
- Pavarani and Savage 1989
- Pavlov 2016
- Paxson 1996
- Payne 1967
- Payne and Henry E. 1961
- Payne and McConnell 2004
- Paynter 1994
- Paynter and Chen 1983
- Paynter et al 1993
- Pařez et al 2025
- Peavey 2000
- Peddle et al 2009
- Pei et al 2018
- Pei et al 2023
- Peloquin et al 2017
- Pelton 1976
- Pelton and Hannah 1976
- Peng and Zhang 2017
- Peng et al 2015
- Peng et al 2018
- Peng et al 2024
- Pennestrì 1992
- Pennington and Meintel 1980
- Penrose and Smith 1996
- Penta et al 2017
- Pereyra and Kung 2026
- Performance Comparison of Counter Rotating Axial Fan and Single 2021
- Perry et al 2018
- Perry et al 2021
- Peteilh et al 2020
- Peters 1985
- Peters and Fottner 2002
- Peterson 1961
- Peterson 1964
- Peterson 1965
- Peterson and Warmbrodt 1986
- Peterson et al 1995
- Petit and Scholey 1973
- Petrescu and Petrescu 2019
- Petrie 1980
- Petrov 1993
- Petrov 1993
- Petruzzelli and Keane 2001
- Peyton Autry 1946
- Pfeifle and Fichter 2021
- Pfeifle and Fichter 2023
- Pfeifle et al 2021
- Pham et al 2020
- Pham Van Bang et al 2022
- Phan and He 2020
- Philhower et al 1998
- Philpot et al 1993
- Pieper 1965
- Pieper et al 2018
- Piipponen et al 2015
- Pikula 2000
- Pinder et al 2001
- Pirera 1983
- Pires et al 2018
- Pisano et al 2025
- Pisaturo and Senatore 2018
- Pisaturo et al 2015
- Pisaturo et al 2016
- Pisaturo et al 2017
- Pitt 1971
- Pittman 1987
- Pizzo 1988
- Place et al 1995
- Platt 1991
- Platzer and Margason 1976
- Plourde et al 1983
- Plumblee 1967
- Podsędkowski et al 2023
- Poggi et al 2024
- Polak and George 1998
- Polat et al 1985
- Pomin and Wagner 2001
- Pomrehn and Papalambros 1993
- Pontika et al 2023
- Poppen et al 1991
- Portapas 2025
- Posnett et al 1986
- Posnett et al 1987
- Postlethwaite 1997
- Postlethwaite 1998
- Postlethwaite and Bates 1998
- Postlethwaite and Bates 1999
- Potonides and Mebes 1984
- Potthast 1982
- Power and Prufert 1996
- Powered-Lift Aerodynamics and Acoustics 1976
- Powers and Robinson 1992
- Powers et al 2015
- Powers et al 2018
- Prabhu et al 2025
- Prahst et al 2015
- Prasad 2025
- Prasad and Choi 2017
- Prasad and Gaitonde 2021
- Prato and Lakshminarayana 1992
- Pratt and Cadou 2026
- Presz and Greitzer 1988
- Presz et al 1994
- Price 1964
- Price 1964
- Price 1981
- Prince and McAulay 1950
- Prochazka and Stomberg 2020
- Prochazka et al 2018
- Proctor et al 2002
- Propeller Slipstream Effects on the Aerodynamics Characteristics of a Transition Micro Air Vehicle 2025
- Propulsion control system designs for advanced Navy multimission aircraft 1990
- Prosek and Barber 1958
- Prothin and Doué 2015
- Prouty 1975
- Prudhomme and Haj-Hariri 1994
- Pruitt and Bates 1992
- Pruyn and Taylor 1971
- Pryce and Hirschberg 2003
- Pryce et al 2005
- Pulk and Stolarik 1977
- Pundhir and Sharma 1992
- Pyle 1947
- Pyle 1971
- Pyszka et al 2023
- Pérez et al 2024
- Qi et al 2001
- Qi et al 2020
- Qi et al 2022
- Qi et al 2024
- Qiang et al 2024
- Qiao and Guo 2021
- Qin 2023
- Qin et al 2023
- Qing et al 2019
- Qing et al 2023
- Qinghuan and Zhiqin 1988
- Qiu 2025
- Qiu and Xu 2021
- Qiu et al 2023
- Qiu et al 2023
- Qiu et al 2023
- Qiu et al 2024
- Qu et al 2016
- Quackenbush et al 1989
- Quackenbush et al 1991
- Quackenbush et al 2019
- Quackenbush et al 2020
- Quillet et al 2023
- Quinn 1973
- Quinn 1973
- Quinto et al 1993
- Rabe et al 1991
- Rabin 1983
- Radermacher et al 2025
- Radil and Berkebile 2020
- Radzman and Uddin 2018
- Rae Jr. 1972
- Raeisi and Alighanbari 2017
- Rafiq and Qureshi 2022
- Rajagopalan 1988
- Rajagopalan and Lim 1991
- Rajendiran Vijayaraj et al 2025
- Rajendran and Pachidis 2020
- Rajeswari and Prabhu 1987
- Rajmohan et al 2015
- Ralin Bukreev 2023
- Rallabhandi and Mavris 2003
- Ramachandran et al 1989
- Ramachandran et al 1989
- Ramanujam and Abhishek 2022
- Ramesh and Subbarao 2016
- Ramsey and Dixon 1967
- Ran 2025
- Rand 1999
- Rand and Khromov 2017
- Ransone 2002
- Rao 1958
- Rao and Saraf 2003
- Rao and Schatzle 1978
- Rapp 1985
- Rathakrishnan 2024
- Rau and Babiceanu 2018
- Ravindranath 2025
- Ray 1983
- Raymer 1998
- Razinsky 1988
- Re and Carson 1991
- Rea et al 2022
- Reda et al 1997
- Reddy et al 1969
- Redondo Gutierrez et al 2022
- Reedy and Gorrell 2025
- Reemsnyder and Sagerser 1979
- Reemsnyder and Sagerser 1979
- Regnier and Nussbaum 2011
- Reichman et al 2016
- Reid and Moore 1978
- Rein and Koch 2015
- Rejeske and Stava 1974
- Rembaut et al 2023
- Ren and Zha 2024
- Ren et al 2024
- Renfroe and Iverson 1986
- Renselaer 1975
- Renselaer 1977
- Representative Operations of V/STOL 2002
- Requirements for STOVL integrated flight/propulsion control system 1994
- Research on Engagement Curve of Clutch Based on Optimization Theory 2018
- Resta et al 2021
- Resta et al 2022
- Resulkulyeva and Serebryansky 2022
- Resulkulyeva and Serebryansky 2023
- Reukauf and Burcham 1976
- Reukauf et al 1975
- Reyhner and Hickcox 1972
- Reyhner and Hickcox 1972
- Rhoades and Ybarra 1980
- Riboldi and Gualdoni 2016
- Riboldi et al 2018
- Ricci et al 2020
- Rice and Locksley 2000
- Richardson 1966
- Richardson and Liiva 1970
- Riddle et al 1981
- Riesenfeld 1968
- Rigbi 1997
- Riggins 1996
- Righetti et al 2017
- Righettini et al 2021
- Rijal et al 2025
- Riley et al 1989
- Rim et al 2016
- Rinehart 1970
- Ringland 1977
- Ritschl et al 2003
- Rizzetta 1991
- Rizzi et al 2025
- Roach and Froning 1996
- Roberts 2002
- Roberts et al 2002
- Roberts et al 2005
- Robinson 1978
- Robinson 2015
- Robinson and High 1974
- Robles Vega et al 2023
- Robson and Lee 2021
- Rock 1989
- Rock 1991
- Rock and Neighbors 1994
- Rock et al 1988
- Rock et al 1994
- Rodgers 2001
- Rodriguez 2004
- Rodriguez and Liscouët-Hanke 2025
- Roelke and Zigan 1972
- Rogers 2002
- Rogers and Belluomini 2026
- Rohan Ramesh et al 2021
- Rohrbach and Wainauski 1981
- Roiati et al 2023
- Rolls and Aoyagi 1977
- Rolls et al 1976
- Roltgen and Byrnes 1991
- Romeu 2018
- Romine and Johnson 1984
- Romine et al 1989
- Rosell and Grönstedt 2026
- Rosen 1972
- Rosen 2004
- Rosen 2004
- Rosenberg 1988
- Rosenberg and Esker 1980
- Rosenberg and Křen 1987
- Rossikhin et al 2018
- Rossow 1985
- Rostami and Farajollahi 2021
- Roth 1993
- Roth 1993
- Roth 1997
- Roth 2001
- Routson et al 1992
- Roy et al 2021
- Rozum 1992
- Ruan et al 2019
- Ruan et al 2025
- Rubel 1978
- Rubel 1978
- Rubel 1982
- Rubinstein 2014
- Rudolph 1972
- Rudowsky et al 2002
- Ruetten 2018
- Ruggeri et al 2017
- Runco et al 2019
- Rusli and Aveka 2021
- Russell and Mattes 1974
- Russo et al 2023
- Ruttledge 1986
- Ryals et al 2026
- Ryan 1966
- Ryan 1986
- Ryan et al 1977
- Ryu et al 2016
- Rönnberg and Duwig 2021
- Rüddenklau and Schitter 2026
- Saari 1958
- Saathoff and Stark 1999
- Saberi et al 2026
- Sabeti and Winter 2024
- Sabeti et al 2024
- Sabo and Drela 2015
- Sabri et al 2021
- Sachs et al 2022
- Saddington and Knowles 1999
- Saddington and Knowles 2001
- Saddington et al 2002
- Saddington et al 2008
- Saddington et al 2009
- Sadiq Ali Mir et al 2025
- Saetti 2025
- Saetti et al 2020
- Safarik and Polak 1996
- Sagan et al 2021
- Sagawa and Ono 2018
- Sagerser et al 1976
- Saghafi and Banazadeh 2006
- Saghafi and Banazadeh 2007
- Saha and Jo 2026
- Saha et al 2026
- Saheby et al 2016
- Saheby et al 2016
- Sahu 1985
- Saini et al 2022
- Sajben 2002
- Sajben 2004
- Sajben and Said 2001
- Sakakibara et al 2001
- Sakamoto and Aihara 2018
- Sakhapov et al 2021
- Salahudden et al 2023
- Salahudden et al 2024
- Salahudden et al 2025
- Salay and Elliott 1993
- Salay and Elliott 1996
- Salazar et al 2020
- Saleem Yusoof et al 2016
- Salehi and Heshmat 2000
- Salisbury 2026
- Salter 1974
- Salter 1975
- Salucci et al 2021
- Samanich and Heidelberg 1976
- Samanich et al 1980
- Samant et al 1983
- Samantaray and Arumuru 2025
- Sambell 1971
- Sambell 1972
- Samimy et al 2011
- Sampaio Felix et al 2023
- Samuel and Lin 2015
- Samuels 1992
- Samuelsson and Grönstedt 2021
- Sanberg et al 1975
- Sanchez-Rivera et al 2020
- Sanders 1964
- Sanders and Laskaridis 2020
- Sanderson and Holly 1993
- Sandlin and Howard 1991
- Sandor et al 1984
- Sandoval and Zhang 2026
- Sandoz et al 2018
- Sanger 1994
- Sankar and Komerath 1988
- Santos et al 2022
- Sarangi and Srinivasan 2022
- Saranyamol et al 2026
- Sarathe and Yadav 2018
- Sargent and Anemaat 2018
- Sarikaya et al 2026
- Saripalli 1981
- Saripalli 1983
- Saripalli 1985
- Saripalli 1995
- Saripalli and Farrell 1993
- Saripalli et al 1997
- Sarup 2026
- Sasamoto 1921
- Sasi et al 2023
- Sasson et al 2015
- Sathish Kumar Sunnam et al. 2019
- Sato et al 2015
- Satria Palar et al 2024
- Saunders and Keith 1991
- Savage et al 2026
- Savino and Zanotti 2025
- Sayari and Bölcs 1995
- Sayma et al 2003
- Scalera and Durham 1999
- Schaefer and Velten 1971
- Schaeffler et al 1967
- Schaub 1974
- Schaub and Krishnappa 1977
- Scheibel et al 2024
- Scheidler 2018
- Schierman and Lowell 1992
- Schierman and Schmidt 1991
- Schierman and Schmidt 1992
- Schierman and Schmidt 1994
- Schiewe et al 2019
- Schirmer and Capone 1989
- Schkolnik 1993
- Schleicher et al 1993
- Schley 1999
- Schlundt 1975
- Schlundt 1976
- Schmid et al 2019
- Schmidt and Schierman 1990
- Schmidt and Staudacher 2015
- Schmidt et al 1993
- Schmidt et al 2021
- Schmitz 1969
- Schmitz 1971
- Schmitz and Vause 1976
- Schneider 1989
- Schneider and Watt 1988
- Schnell 1982
- Schnell and Grossman 1978
- Schnerr and Dohrmann 1991
- Schnerr and Dohrmann 1994
- Scholtz and Trass 1970
- Scholz et al 2021
- Scholz et al 2022
- Schrage and Patel 2019
- Schreiber et al 2017
- Schroeder and Merrick 1990
- Schroers and Antoniou 1964
- Schroeter et al 2024
- Schröder and Schuster 1972
- Schuster and Flood 1978
- Schwaar 1961
- Schwagerus et al 2026
- Schwartz 1975
- Schwartz 1988
- Schwartz and Shearer 1964
- Schwartz et al 2024
- Scientific and Technical Information Division 1966
- Scopes 2001
- Scordamaglia et al 2025
- Sears and Bajek 1958
- Secchi et al 2019
- Secchi et al 2021
- Sedgwick 1975
- Sedlock 1985
- Seidel and Matwey 1983
- Seidel and Peters 2019
- Seidel et al 1980
- Seider and Haenel 1991
- Seiler and Schum 1978
- Seiler and Schum 1979
- Seiner and Gilinsky 1995
- Seiner et al 1988
- Seitz 1975
- Seitz and Goodson 1973
- Sellers 1973
- Sellers and Szuch 1973
- Sellers et al 1977
- Semelka and Rauleder 2026
- Sementi 2002
- Semiletov and Karabasov 2016
- Semmes and Weyer 1990
- Senkans et al 2021
- Senthil Kumar et al 2018
- Seo and Kim 2016
- Seo et al 2020
- Seo et al 2021
- Sepulveda and Smith 2019
- Serkin 2025
- Serovy and Kavanagh 1974
- Serrano et al 2021
- Sevich and Beattie 1974
- Shaft-driven motor couplings 1995
- Shah and Bilgen 2023
- Shahmiri 2017
- Shanbhag and Narasimha 1970
- Shang et al 2021
- Shanks et al 1993
- Shanks et al 2018
- Shannak and Alhasan 2002
- Shao et al 2023
- Sharif 2015
- Sharjad et al 2022
- Sharma et al 1987
- Sharma et al 1991
- Sharma et al 2020
- Sharma et al 2021
- Sharon 1975
- Sharpe and Agarwal 2019
- Sharpe and Hansman 2024
- Shaw et al 1987
- Shearwood et al 2020
- Shebl 2026
- Shehadeh et al 2004
- Sheikhpour and Bamdad 2017
- Sheng 2018
- Sheng and Sun 2015
- Sheng and Zhao 2016
- Sheng and Zhao 2017
- Sheng and Zhao 2022
- Sheng and Zhao 2025
- Sheng and Zhao 2026
- Sheng et al 2015
- Sheng et al 2015
- Sheng et al 2016
- Sheng et al 2018
- Sheng et al 2022
- Sheng et al 2025
- Shenoy and Gray 1981
- Sheplak and Spina 1993
- Sheridan 1983
- Sheridan 1986
- Sherman 1964
- Sherman and Usab 1974
- Sherza 2019
- Sherza et al 2018
- Sherza et al 2022
- Sherzaa et al 2022
- Shevchenko and Pavlov 2018
- Shevchenko et al 2017
- Shevchenko et al 2019
- Shi and Yu 2023
- Shi et al 2002
- Shi et al 2023
- Shi et al 2024
- Shi et al 2024
- Shi et al 2026
- Shin and Choi 2024
- Shin and Lee 2023
- Shinoda et al 2016
- Shinozuka et al 2024
- Shipman and Bin 2021
- Shiryaev and Serebryansky 2022
- Shishir et al 2001
- Shivananda et al 1978
- Shivaramaiah and Varpe 2023
- Shivashankara et al 1990
- Shivdas et al 2019
- Shivers 1961
- Shmilovich and Yadlin 2020
- Shovlin 1978
- Shovlin et al 1979
- Showers 1980
- Shrestha et al 2016
- Shubert and Sizoo 2025
- Shucheng and Xijun 1994
- Shujun 1990
- Shukla et al 2022
- Shukla et al 2026
- Shuo et al 2025
- Shur et al 2016
- Shur et al 2018
- Si et al 2016
- Siba et al 1998
- Sibulkin 1964
- Siclari et al 1975
- Siclari et al 1976
- Siclari et al 1977
- Siddavatam et al 2023
- Siddharth et al 2026
- Sigal 1988
- Silva
- Silva et al 2017
- Silva et al 2019
- Silva-Martinez et al 2015
- Sim 2025
- Simmons 2022
- Simmons 2023
- Simmons 2023
- Simmons and Murphy 2021
- Simmons and Murphy 2022
- Simmons et al 2021
- Simmons et al 2023
- Simon 2024
- Simon and Bohn 1974
- Simon et al 2023
- Simpson 1972
- Simpson 1979
- Simpson 1986
- Simpson 2003
- Simsek et al 2016
- Simulation of Rotor-Rotor Interaction and Noise of an Axial Counter-Rotating Fan 2023
- Sinacori 1970
- Sinacori 1970
- Singh 1974
- Singh 2022
- Singh 2026
- Singh and Friedmann 2018
- Singh and Kushari 2008
- Singh et al 2024
- Sinha 1988
- Sisson and Dogan 2025
- Sisson et al 2024
- Sitaram 1988
- Sivaramakrishnan 1981
- Sivrioğlu 2023
- Skelton 1968
- Skira et al 1980
- Skvortsov 2016
- Slater 2001
- Slater 2019
- Smetana and Knepper 1973
- Smith 1958
- Smith 1961
- Smith 1961
- Smith 1966
- Smith 1966
- Smith 1968
- Smith 1983
- Smith 1996
- Smith 1996
- Smith 1997
- Smith 1997
- Smith 1997
- Smith and Berry 2000
- Smith and McArdle 1990
- Smith and McArdle 1992
- Smith and Meyer 1981
- Smith and Wehofer 1982
- Smith et al 1973
- Smith et al 1979
- Smith et al 1991
- Smith et al 1992
- Smith et al 1993
- Smith et al 1993
- Smith et al 1994
- Smith et al 1999
- Smith et al 2026
- Snyder 1950
- Snyder 2020
- Sobel 2013
- Sobel and Lallman 1988
- Soderman 1990
- Soderman and Foster 1988
- Sokhey et al 2002
- Solies 1992
- Solnyshkin 2024
- Soltani and Askari 2018
- SoltanRezaee et al 2021
- Soltis and Sangeorzan 2015
- Solvey 1951
- Son and Kim 2023
- Song and Sun 2017
- Song et al 2026
- Sonkar et al 2021
- Sorbilli et al 2018
- Sorensen and Bencze 1973
- Sorensen and Cuppoletti 2022
- Sorensen and Cuppoletti 2022
- Sorensen and Latham 1975
- Sorensen and Smeltzer 1972
- Sorensen et al 1973
- Sorensen et al 2024
- Sotheran 1982
- Soudakov 2016
- Soufivand et al 2024
- Sova 1988
- Sowers 1965
- Soylu and Burak Akbulut 1997
- Spaans et al 2024
- Spadão et al 2026
- Spannagl and Ducard 2020
- Sparrow and Lee 1975
- Sparrow et al 1975
- Speakman et al 1978
- Spearman 1979
- Spearman 1984
- Speir and Blozy 1981
- Spencer et al 1969
- Spratt 1990
- Squire and Nasser 1993
- Sreeletha et al 2019
- Sridhar and Smith 2026
- Sridhar et al 2025
- Sridharan and Govindarajan 2022
- Srinathkumar 2019
- Srinivasan and McCroskey 1988
- Srivastava et al 2025
- Srivatsan et al 1986
- St. Aubyn 2015
- Stahl et al 2018
- Stalder et al 1950
- Stam and de Visser 2025
- Stamm and Woods 2024
- Stanley 1980
- Stanly et al 2020
- Stanniland 1974
- Stapleford 1980
- Stapountzis 1993
- Stark 2003
- Starr and Varner 1976
- Staruk and Datta 2019
- Staruk et al 2017
- Staruk et al 2020
- Stauffer et al 1990
- Steele and Aurora 1978
- Steger and Baldwin 1973
- Steils 1965
- Stenberg 1983
- Stephens et al 2019
- Stepniewski 1940
- Stepniewski 1959
- Sternfeld and Hinterkeuser 1970
- Stevens et al 2015
- Stewart 1979
- Stewart 1980
- Stewart 1992
- Stewart and Blake 1992
- Stewart and Blake 1993
- Stewart and Paulson 1984
- Stewart et al 1992
- Stewart et al 2011
- Stewart et al 2026
- Stockman et al 1973
- Stockman et al 1974
- STOL, VTOL, and V/STOL 1971
- Stoll and Veble Mikić 2022
- Stone 1958
- Stone 2013
- Stone and Gutierrez 1972
- Stortz and O’Donoghue 1993
- Straight and Cullom 1982
- Strand 1967
- Strand et al 1967
- Strand et al 1967
- Strash et al 1997
- Strash et al 2000
- Strathoff et al 2020
- Strawn and Djomehri 2002
- Strazisar et al 1989
- Streets 1960
- Streets 1963
- Streiff and Henderson 1974
- Stricklin and Hess 1969
- Striegl and Diller 1984
- Striegl and Diller 1984
- Structural Design of the 1969
- Struth 1999
- Stubbs 1956
- Stuermer et al 2022
- Stutz and Price 1964
- Su and Rauleder 2026
- Su et al 2022
- Su et al 2023
- Su et al 2025
- Su et al 2025
- Su et al 2026
- Sudasinghe et al 2022
- Suder 2019
- Suder et al 1987
- Sudhan and Vasanthan 2021
- Suh 1990
- Suharev et al 2019
- Suiçmez and Kutay 2023
- Sulkoske et al 1977
- Sullivan 1990
- Sullivan and Hager 1983
- Sullivan and Murthy 1990
- Sully and Whittley 1987
- Sun and de Visser 2019
- Sun and Hansen 1982
- Sun and Pang 2025
- Sun et al 2015
- Sun et al 2016
- Sun et al 2017
- Sun et al 2021
- Sun et al 2025
- Sun et al 2025
- Sun et al 2025
- Sun et al 2026
- Supersonic flow computations for an ASTOVL aircraft configuration 1990
- Surapaneni et al 2016
- Surber 1975
- Surber and Robinson 1983
- Surber and Sedlock 1978
- Suresh et al 2026
- Surmann et al 2024
- Susilo et al 2024
- Suzuki and Kuno 1995
- Suñol Jiménez et al 2015
- Svoboda 2000
- Swaim 1970
- Swamy et al 1978
- Swan 1961
- Swanson 1993
- Swavely and Soileau 1972
- Sweep Optimization to Reduce Aerodynamic Loss in a Transonic Axial Compressor with Upstream Boundary Layer Ingestion 2024
- Swortzel and Barfield 1976
- Syamsuar 2017
- Syberg et al 1980
- Sylvester et al 2011
- Synodinos et al 2018
- Synodinos et al 2024
- Synylo et al 2020
- Szadkowski and McNerney 1992
- Szadkowski and Morford 1992
- Szlenkier 1972
- Sóbester 2021
- Sørensen et al 1996
- T-4 inlet/engine compatibility flight test results 1989
- Tabanli and Yuceil 2021
- Tacina et al 2004
- Taflan et al 2024
- Tafti and Vanka 1990
- Taghinia and Rahman 2018
- Takahashi 2021
- Takahashi 2022
- Takahashi 2026
- Takallu and Gentry 1992
- Takamatu and Takezako 1967
- Takeyeldein 2026
- Takovitskii 2020
- Tam 2015
- Tamm and Spyropoulos 2018
- Tamrat 1988
- Tan et al 2018
- Tan et al 2018
- Tan et al 2019
- Tan et al 2023
- Tanakitkorn et al 2017
- Tanakitkorn et al 2017
- Tang et al 2021
- Tang et al 2025
- Tang et al 2026
- Taniguchi and Oyama 2022
- Tanveer and Ahmad 2023
- Tape and McIntyre 1990
- Tariq and Nahon 2020
- Tariq et al 2019
- Tatar and Schwingshackl 2018
- Tate and Gillard 1975
- Tatenda and Qiang 2023
- Tauber et al 1976
- Tavkhelidze and Davitashvili 1974
- Tawfek 1996
- Taylor 1968
- Taylor 1968
- Taylor 1988
- Taylor et al 1973
- Taylor et al 2004
- Taymourtash et al 2021
- Taymourtash et al 2021
- Tchavdarov 1997
- Teel 1999
- Teel 1999
- Tekaslan et al 2021
- Terauchi et al 1981
- Terrier and Lu 2003
- Tesch 1971
- Tesch and Pase 1983
- Thakur and Kumar 2021
- THE CENTRIFUGAL COMPRESSOR STAGE 1964
- The Hawker P1127 vectored thrust fighter program - Lessons learned 1990
- The Integrated Flight and Powerplant Control System Demonstration programme 1993
- The model of friction for dry clutch working process simulation 2020
- The normal impingement of a circular air jet on a flat surface 1962
- The verification of inlet/engine distortion compatibility 1988
- Theilliol et al 2015
- THEORETICAL FOUNDATION OF FORMATION OF AIRCRAFT WEIGHT APPEARANCE 2021
- Thompson and Epstein 1977
- Thompson and Smith 1981
- Thompson et al 1988
- Throndson 1973
- Throndson 1982
- Throneberry et al 2022
- THRUST VECTORING OF A SUPERSONIC RECTANGULAR NOZZLE BY USING DIFFERENT PLATE EXTENSIONS 2020
- Tian et al 2018
- Tian et al 2025
- Tibabisco et al 2019
- Tich 1991
- Tidow and Rudnik 2025
- Tillman and Ikeler 1991
- Tillman and Presz 1993
- Tindell 1973
- Tindell 1980
- Tindell 1987
- Tindell and Flynn 1978
- Tiwari et al 2024
- Toenskoetter 1984
- Toha et al 2015
- Tohidi and Yildiz 2021
- Tohidi et al 2017
- Tohidi et al 2018
- Tohidi et al 2021
- Tong and Yanagita 2019
- Topczewska et al 2020
- Torenbeek 1972
- Touyeras and Villain 2004
- Tran and Lim 2022
- Tran and Yeo 2023
- Tran et al 2023
- Transition aerodynamics for close-coupled wing-canard configuration<149>V/STOL operations 1979
- Traub 2016
- Trazzi 2004
- Trefny and Wasserbauer 1986
- Trobaugh and Obrimski 1980
- Trost and Schnell 2025
- Troudet et al 1991
- True 1967
- Truong and Papamoschou 2015
- Tsai and Roth 2001
- Tsentis et al 2023
- Tsuboi et al 1991
- Tsubokura et al 1998
- Tu and Wood 1996
- Tudosie 2017
- Tudosie 2017
- Tudosie 2018
- Tudosie and Prisacariu 2022
- Tullu and Jung 2026
- Tumelero Valente et al 2023
- Turner et al 2001
- Turner et al 2015
- Turney and Allen 1980
- Tutulan et al 2004
- Uehara et al 2019
- Uenishi et al 1992
- Uhuad and Franke 1993
- Ulizar 1997
- Umeyama et al 1998
- Universal Energy Systems Inc Dayton Oh 1995
- Upadhyay and Zaman 2019
- Uppaluri and Douglass 1991
- Urakubo et al 2023
- Uranga et al 2018
- Urasek and Moore 1972
- Urbinati and Pennestrì 1998
- V/STOL propulsion control analysis 1981
- V/STOL World wide view 1971
- VAAC Harrier trials 2001
- Vadyak and Atta 1985
- Vadyak et al 1987
- Vagianos and Rooney 1964
- Vahid Amirinezhad and Uyguroğlu 2015
- Vaidyanathan et al 1994
- Valencia et al 2015
- Valencia et al 2019
- Valenti and Stanton 2024
- Van Dalsem et al 1990
- van Dam et al 1995
- van der Vooren and van der Wees 1991
- van Es 1999
- van Kuik et al 2015
- Van Nieuwstadt and Murray 1998
- Van Riper and Wood 2003
- Van Zante et al 2002
- Vance 1973
- Vandalsem et al 1989
- Vanderlip and Schneider 1963
- Vanka 1998
- Vanoverbeke and Holdeman 1988
- VanOverbeke and Holdeman 1990
- VanSchalkwyk et al 2001
- Vasanthakumar et al 2019
- Vassilopoulos 1988
- Vectored thrust 1992
- Vegh 2025
- Velkoff et al 1971
- Vella et al 2026
- Vepa 2021
- Veres 2001
- Verghese 2023
- Verma 2018
- Vernyi et al 2026
- Vertical Takeoff and Landing 2014
- Vertical/short takeoff and landing
- Vieira et al 2025
- Viets 1974
- Viets 1977
- Vigano et al 2024
- Vile et al 2019
- Vile et al 2019
- Vile et al 2020
- Vinay et al 2022
- Vinayagam and Sinha 2023
- Vincent and Anex 1990
- Vinje and Miller 1973
- Vinz and Raichle 2024
- Vipin and Vijayakumar 2022
- Viswanath 1988
- Viswanath and Rajendra 1990
- Vitale et al 2023
- Vizzini 1985
- Vogeley 1948
- Vohra and Kumar 2025
- Volkov et al 2022
- Volpe and Jameson 1990
- von Backstroem et al 2000
- Von Glahn and Groesbeck 1979
- von Hlatky and Rice 2018
- Voracek 1990
- Voskuijl et al 2018
- Vouros et al 2022
- Vozka et al 2019
- VSTOL Systems Research Aircraft 1994
- Vu and Lee 2015
- Vu et al 2026
- Vucetic 2010
- Vucetic 2013
- Vucetic and Nossal 2013
- Vyrabov 1991
- Waanders and Rauleder 2026
- Wachspress et al 2026
- Wada et al 2022
- Waddington et al 2023
- Wadia and Law 1992
- Wadia et al 2018
- Waesche and Midgal 1975
- Wahl and Julian 1956
- Wahler et al 2023
- Wahler et al 2025
- Wainauski and Vaczy 1986
- Waithe and Deere 2003
- Wakefield et al 2019
- Walitt et al 1997
- Walker 1955
- Walker 1964
- Walker and Allen 2002
- Walkley 1986
- Wall 1989
- Wall and Meyer 2017
- Wall and Meyer 2020
- Wall et al 2017
- Wallace and Bowers 1982
- Wallace et al 2025
- Walsh et al 2016
- Walter et al 2016
- Walter et al 2023
- Walter et al 2023
- Walvekar and Chakravarthy 2022
- Walvekar and Chakravarthy 2023
- Walz 1976
- Wang 2003
- Wang 2026
- Wang and Gosselin 1996
- Wang and Hu 2026
- Wang and Jin 2025
- Wang and Ma 2021
- Wang and Mesbahi 2021
- Wang and Peterson 1958
- Wang and Wang 2020
- Wang and Zhang 2022
- Wang and Zhu 2020
- Wang and Zhu 2021
- Wang et al 2007
- Wang et al 2014
- Wang et al 2017
- Wang et al 2017
- Wang et al 2018
- Wang et al 2018
- Wang et al 2019
- Wang et al 2020
- Wang et al 2020
- Wang et al 2021
- Wang et al 2021
- Wang et al 2021
- Wang et al 2021
- Wang et al 2022
- Wang et al 2022
- Wang et al 2022
- Wang et al 2022
- Wang et al 2022
- Wang et al 2023
- Wang et al 2023
- Wang et al 2023
- Wang et al 2023
- Wang et al 2024
- Wang et al 2024
- Wang et al 2024
- Wang et al 2024
- Wang et al 2024
- Wang et al 2025
- Wang et al 2025
- Wang et al 2025
- Wang et al 2026
- Wang et al 2026
- Wang et al 2026
- Wang Fawei 2016
- Warakomski 1979
- Ward 1968
- Ward 1983
- Ward 1989
- Ward and Lewis 1987
- Ward and Mahmood 1982
- Ward and Neeley 1959
- Ward and Penrose 1983
- Wardwell and Hange 1993
- Wardwell et al 1986
- Wardwell et al 1992
- Wardwell et al 1993
- Ware et al 1974
- Wareing 1968
- Warmbrodt and Hull 1982
- Warner et al 1986
- Warren and Floden 2001
- Warsett 1953
- Warsop et al 2019
- Watanabe et al 1993
- Watanabe et al 1998
- Watanabe et al 2001
- Waters et al 2015
- Watkins 2019
- Watson 1980
- Watson 1981
- Watson et al 1986
- Watson et al 2019
- Watts et al 1993
- Weber 1960
- Weber 1960
- Weber 1961
- Weber 1982
- Weber and Williams 1978
- Webster 1971
- Webster et al 1995
- Wechtler et al 2025
- Weeks 1986
- Wegener 1977
- Wei 2016
- Wei and Kun 2015
- Wei and Zhong 1988
- Wei et al 2019
- Wei et al 2021
- Wei et al 2024
- Wei et al 2025
- Wei et al 2025
- Wei et al 2026
- Wei Yuan and Katupitiya 2013
- Wei-Liang and Qi-Xian 1989
- Wei-rong and Xing-yong 1989
- Weightman et al 2016
- Weilenmann and Geering 1993
- Weinstein and Simmons 2024
- Weinstein et al 1986
- Wells 2002
- Wells and Urnes 1995
- Wells et al 1989
- Wen et al 2016
- Wen et al 2020
- Wennerstrom 1984
- Wennerstrom 1987
- Wennerstrom and Frost 1974
- Werner et al 2022
- Wernicke 1981
- West 1969
- Westcott et al 2023
- Westcott et al 2025
- Whatley et al 1990
- Wheeler et al 2021
- White et al 1960
- White et al 1985
- Whitehead 1986
- Whitehead and Davies 1983
- Whiteside et al 2021
- Whitfield and Blackburn 1965
- Whitford 1990
- Whitford 1991
- Whitford 1994
- Whitford 1995
- Whitley et al 1996
- Whoric 1977
- Wichert 1961
- Wichita State Univ Ks 1962
- Wickert 1985
- Wickman 1953
- Widmayer and Tomassoni 1971
- Wildermuth et al 1974
- Wildermuth et al 1974
- Wilken 1991
- Willhite et al 1995
- Williams and Bernitt 1970
- Williams and Hunt 1980
- Williams and Vittal 2002
- Willis 1980
- Willis 1980
- Willis and Beard 2022
- Willis and Genever-Watling 1977
- Willis and Welliver 1976
- Willis et al 1982
- Willshire and Martin 1984
- Wilson and Liperra 1984
- Wilson and Mahoney 1988
- Wilson and White 1993
- Wilson and Wurts 1985
- Wilson et al 1981
- Wilson et al 1985
- Wilson et al 1997
- Wilson et al 2003
- Winborn 1970
- Winbush and James O. 2012
- Wind tunnel and ground 1976
- Winfree 1998
- Wing and Asbury 1991
- Wing and Giuliano 1997
- Winick 1968
- Winkler 2015
- Winkler 2017
- Winkler 2019
- Winkler 2022
- Winkler and Crowe 2019
- Winkler and Davis 2017
- Winston et al 1975
- Winter and Paul 1985
- Wise et al 1999
- Witkowska and Śmierzchalski 2018
- Witte 1969
- Wittenberg 2001
- Wittig et al 1994
- Wlezien and Ferraro 1990
- Wlezien and Ferraro 1992
- Woehler et al 2023
- Woelk 1989
- Wohllebe and Migdal 1979
- Wolfshtein 1970
- Wolter et al 2017
- Wolters et al 2016
- Wood 1968
- Wood 2001
- Wood and Hammam 2022
- Woodward 1992
- Woodward and Glaser 1976
- Woollett 1983
- Wooten et al 1984
- Worden et al 2016
- Wright and Jones 1970
- Wright and Seitz 2019
- Wright and Silva 2026
- Wright et al 1973
- Wroblewski and Ansell 2018
- Wroblewski and Ansell 2020
- Wu 1973
- Wu and Chow 1985
- Wu et al 2001
- Wu et al 2019
- Wu et al 2021
- Wu et al 2021
- Wu et al 2022
- Wu et al 2023
- Wu et al 2023
- Wu et al 2024
- Wu et al 2025
- Wu et al 2025
- Wu et al 2026
- Wu et al 2026
- Wyss et al 1993
- Xia et al 2020
- Xiang et al 2015
- Xiang et al 2016
- Xiang et al 2023
- Xiang et al 2025
- Xiang et al 2025
- Xiangyang et al 2019
- Xiao et al 2024
- Xiaolong et al 2018
- Xiaozeng et al 2015
- Xie and Haberland 1999
- Xie et al 2016
- Xie et al 2020
- Xie et al 2021
- Xie et al 2023
- Xie et al 2026
- Xu and Zha 2020
- Xu et al 2016
- Xu et al 2016
- Xu et al 2017
- Xu et al 2018
- Xu et al 2023
- Xu et al 2024
- Xu et al 2025
- Xu et al 2025
- Xu et al 2026
- Xu et al 2027
- Xue and Atkins 2003
- Xue et al 2024
- Xue et al 2026
- Yackle 1992
- Yajnik and Subbaiah 1976
- Yamato et al 1988
- Yamato et al 1991
- Yang and Gao 2020
- Yang and Morales 2021
- Yang and Tan 2025
- Yang and Yao 1992
- Yang and Zhuang 2000
- Yang et al 1985
- Yang et al 1992
- Yang et al 1998
- Yang et al 2023
- Yang et al 2024
- Yang et al 2024
- Yang et al 2024
- Yang et al 2025
- Yang et al 2025
- Yang et al 2026
- Yang et al 2026
- Yangang et al 2015
- Yangping and Honggang 2018
- Yao and Li 2024
- Yao et al 2015
- YAV-8B reaction control system bleed and control power usage in hover and transition 1993
- Ye et al 2024
- Yechout 1988
- Yeh 1959
- Yeh et al 1993
- Yen 1981
- Yeo and Johnson 2015
- Yeo and Saberi 2020
- Yi et al 1979
- Yiming et al 2019
- Yin 2019
- Yin et al 2001
- Yin et al 2019
- Yiting et al 2021
- Yokell and Baker 1994
- Yokota and Fujimoto 2022
- Yon and Li 2026
- Yonke et al 1985
- Yoo et al 2024
- Yoshida et al 2021
- Yoshihara 1963
- Yotov Daskalov 1990
- You et al 2026
- Younes and Hickey 2020
- Young 2023
- Young et al 1995
- Yu 2023
- Yu et al 1983
- Yu et al 2002
- Yu et al 2018
- Yu et al 2018
- Yu et al 2021
- Yu et al 2021
- Yu et al 2022
- Yu et al 2025
- Yu et al 2026
- Yu Luo et al 2004
- Yu-bing et al 1981
- Yuan et al 2023
- Yuan et al 2024
- Yuan et al 2024
- Yue et al 2015
- Yue et al 2015
- Yuksel and Aygün 2025
- Yungster 2003
- Yurt et al 2026
- Yılmaz and German 2024
- Zabinsky and Burnham 1977
- Zabinsky et al 1975
- Zaffran and Erwes 2015
- Zafi and Chakraborty 2023
- Zafirov 2010
- Zagrodzki and Truncone 2003
- Zahaby 1979
- Zakaria et al 2019
- Zaki et al 2017
- Zalay et al 1980
- Zaludin 2024
- Zaludin and Gires 2019
- Zaludin and Harituddin 2019
- Zaludin et al 2021
- Zangeneh et al 2004
- Zanotti and Algarotti 2022
- Zanotti et al 2024
- Zawodny et al 2022
- Zebbiche and Youbi 2023
- Zein-Sabatto et al 2017
- Zeng and Guedes Soares 2025
- Zha and Ren 2023
- Zha et al 2024
- Zhang and Agarwal 2020
- Zhang and Engeda 2018
- Zhang and Ibrahim 2004
- Zhang and Ing 1993
- Zhang and Ing 1994
- Zhang and Lin 2018
- Zhang and Liu 2024
- Zhang and Qi 2024
- Zhang and Vahdati 2018
- Zhang and Vahdati 2019
- Zhang and Wei 2015
- Zhang and Yao 2019
- Zhang et al 2015
- Zhang et al 2015
- Zhang et al 2015
- Zhang et al 2015
- Zhang et al 2016
- Zhang et al 2017
- Zhang et al 2018
- Zhang et al 2019
- Zhang et al 2019
- Zhang et al 2019
- Zhang et al 2019
- Zhang et al 2019
- Zhang et al 2020
- Zhang et al 2020
- Zhang et al 2020
- Zhang et al 2021
- Zhang et al 2021
- Zhang et al 2021
- Zhang et al 2021
- Zhang et al 2021
- Zhang et al 2023
- Zhang et al 2024
- Zhang et al 2024
- Zhang et al 2024
- Zhang et al 2025
- Zhang et al 2025
- Zhang et al 2025
- Zhang et al 2025
- Zhang et al 2025
- Zhang et al 2026
- Zhang et al 2026
- Zhao 2018
- Zhao and Li 2018
- Zhao and Wang 2016
- Zhao et al 2015
- Zhao et al 2018
- Zhao et al 2020
- Zhao et al 2022
- Zhao et al 2023
- Zhao et al 2023
- Zhao et al 2024
- Zhao et al 2024
- Zhao et al 2025
- Zhao et al 2025
- Zhao et al 2025
- Zhao et al 2025
- Zhao et al 2026
- Zhao et al 2026
- Zhao et al 2026
- Zheng et al 2023
- Zheng et al 2025
- Zhipeng et al 2015
- Zhong et al 2019
- Zhonghua and Haitao 2021
- Zhou and Fenton 1992
- Zhou and Xi 1998
- Zhou and Xin 2020
- Zhou et al 1995
- Zhou et al 2018
- Zhou et al 2019
- Zhou et al 2020
- Zhou et al 2022
- Zhou et al 2022
- Zhou et al 2025
- Zhu and Zhao 2015
- Zhu et al 2016
- Zhu et al 2020
- Zhu et al 2021
- Zhu et al 2023
- Zhu et al 2025
- Zhu et al 2026
- Zikyamov and Panayotov 2025
- Zilz and Bailey 1985
- Zimbelman and Rouser 2025
- Zimmer et al 2015
- Ziogas et al 2025
- Zistler et al 2025
- Zlatanov et al 1992
- Zmijanovic
- Zola et al 1984
- Zoppelt et al 2024
- Zou 2022
- Zou et al 1996
- Zsolt 2018
- Zukoski and Auerbach 1976
- Öhrle et al 2019
- Özgören 1999
- Łukasik 2017
- Šajbanová and Čerňan 2021
- Šajbanová et al 2021
Referenced by
- X-Planes: Synthesis and What the Designation Became 2025-12-16
- X-Planes: Bell Textron X-76 SPRINT 2025-12-15
- X-Planes: X-69 through X-75, the Leapfrogged Block 2025-12-14
- X-Planes: General Atomics X-68 LongShot 2025-12-13
- X-Planes: X-67, the Slot Taken by XQ-67A 2025-12-12
- X-Planes: Boeing X-66 2025-12-11
- X-Planes: Aurora Flight Sciences X-65 CRANE 2025-12-10
- X-Planes: Invocon X-64 2025-12-09
- X-Planes: ABL Space Systems X-63 2025-12-08
- X-Planes: Lockheed Martin X-62 VISTA 2025-12-07
- X-Planes: Dynetics X-61 Gremlins 2025-12-06
- X-Planes: Generation Orbit X-60 2025-12-05
- X-Planes: Lockheed Martin X-59 Quesst 2025-12-04
- X-Planes: X-58, the Slot Taken by XQ-58 2025-12-03
- X-Planes: ESAero X-57 Maxwell 2025-12-02
- X-Planes: Lockheed Martin X-56 2025-12-01
- X-Planes: Lockheed Martin X-55 ACCA 2025-11-30
- X-Planes: Gulfstream X-54 2025-11-29
- X-Planes: Boeing X-53 Active Aeroelastic Wing 2025-11-28
- X-Planes: X-52, the Designation Refused 2025-11-27
- X-Planes: Boeing X-51 Waverider 2025-11-26
- X-Planes: Boeing X-50 Dragonfly 2025-11-25
- X-Planes: Piasecki X-49 SpeedHawk 2025-11-24
- X-Planes: Boeing X-48 2025-11-23
- X-Planes: Northrop Grumman X-47 2025-11-22
- X-Planes: Boeing X-46 2025-11-21
- X-Planes: Boeing X-45 2025-11-20
- X-Planes: X-44, One Designation and Two Aircraft 2025-11-19
- X-Planes: Micro-Craft X-43 Hyper-X 2025-11-18
- X-Planes: Orbital Sciences X-42 2025-11-17
- X-Planes: X-41 Common Aero Vehicle 2025-11-16
- X-Planes: Boeing X-40 2025-11-15
- X-Planes: X-39, Reserved but Never Assigned 2025-11-14
- X-Planes: Scaled Composites X-38 2025-11-13
- X-Planes: Boeing X-37 2025-11-12
- X-Planes: McDonnell Douglas X-36 2025-11-11