X-Planes: Schweizer X-26 Frigate

Nov 1, 2025 • 576 min read • 126788 words • Comments

Filed under: aerospace, history, engineering

The Schweizer SGS 2-32 is a two-seat sailplane of 1962, built in Elmira, New York, sold to soaring clubs, and about as far from a research aeroplane as an aircraft can be. The United States military took it up twice, gave it the same X-designation both times, and used it for two purposes that have nothing to do with each other. This article is the twenty-seventh 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, and the X-25.

As the X-26A it was flown unmodified at the Naval Test Pilot School to teach student test pilots what adverse yaw feels like. As the X-26B it was the QT-2, for Quiet Thruster, a silenced engine and a slow-turning propeller wrapped around the same airframe, flown over the Mekong Delta at night in 1968 to watch the ground without being heard.

Both share a single designation, X-26.

One of those programmes wanted the aircraft’s worst handling trait to be as obvious as possible. The other wanted the aircraft to be as close to absent as possible. They are opposite requirements and they were met by the same airframe, because both of them are consequences of a single number.

The Research Question

There are two, and the article’s argument is that they have the same answer.

Can a student test pilot be taught to recognise adverse yaw before it matters? A jet trainer exhibits the phenomenon, but presents it in a fraction of a second and at small amplitude, which teaches nothing to anyone who does not already know what happened.

Can a manned aircraft loiter over hostile ground at night without being heard? That is a question about acoustics, about power, and in the end about how quiet the night is.

The binding constraint in both cases is the lift-to-drag ratio, which for a wing of aspect ratio $A$ and zero-lift drag coefficient $C_{D_0}$ is

\[\left( \frac{L}{D} \right)_{max} = \frac{1}{2} \sqrt{\frac{\pi e A}{C_{D_0}}} \tag{1}\]

Read one way that relation says a high lift-to-drag ratio demands a long slender wing, and a long slender wing flown slowly is what produces large adverse yaw. Read the other way, through the power required to sustain flight, it says a high lift-to-drag ratio demands very little power, and an engine that is barely working can be silenced.

The same property, pushed to an extreme by people who wanted neither of these things, produced both.

Programme Origin

Schweizer Aircraft of Elmira built sailplanes for the American soaring market from the 1930s. The SGS 2-32 was its high-performance two-seater, and by the standards of production sailplanes it was large, heavy and very clean.

The Navy’s problem was pedagogical. Yaw-roll coupling, and the Dutch roll mode it feeds, is a phenomenon every student test pilot at Patuxent River would meet, and conventional jet trainers presented it too quickly and too dangerously for effective instruction. The school wanted an aircraft that exhibited the same physics slowly. Four were ordered as the X-26A.

The Army’s problem was operational. Night observation over the Delta required an aircraft that could loiter low without announcing itself, and the Army specification to which the production YO-3A was later designed asked for acoustic undetectability at 1,500 feet. Lockheed Missiles and Space Company took two X-26A airframes, serials 67-15345 and 67-15346, and rebuilt them as the QT-2, which in its Prize Crew form became the QT-2PC.

Neither programme was a Schweizer initiative and neither aircraft was developed as a research vehicle.

The Vehicles

	X-26A	X-26B
Basis	Schweizer SGS 2-32, unmodified	SGS 2-32 rebuilt as QT-2 and QT-2PC
Role	flying qualities instruction	night observation
Operator	United States Naval Test Pilot School	United States Army, in Vietnam
Power	none	Continental O-200, 100 horsepower
Propeller	none	four-blade wooden, on an extension shaft
Number	four ordered, with replacements	two converted

Specifications of the airframe both share, from the sailplane and X-26A records.

Quantity	Value
Span	57 ft 1.5 in
Wing area	180 sq ft
Aspect ratio	18.05
Empty weight	857 lb
Gross weight	1,430 lb
Best glide ratio	35 at 55.9 mph
Minimum sink	124 ft/min

Three of the four X-26A airframes were lost and replaced. For a docile sailplane operated by a test pilot school that record deserves attention, and Where the Framing Breaks Down returns to it.

The X-26A outlasted almost every other aircraft in this series. It remained in service at the Test Pilot School for decades after the X-25, the X-24 and the rest had been retired, because the phenomenon it demonstrates did not change and neither did the cheapest way to demonstrate it.

Sizing From First Principles

The One Relation

Everything in this article comes out of one relation. The drag of a wing is a constant term plus a term that lift itself creates,

\[C_D = C_{D_0} + \frac{C_L^2}{\pi e A} \tag{2}\]

The second term is the common root of the article’s two subjects. It is what makes the lift-to-drag ratio high, because it falls as aspect ratio rises. It also makes a rolling wing drag asymmetrically, and that asymmetry is the adverse yaw the Naval Test Pilot School wanted to demonstrate. The literature of induced drag includes Sibert 1943, Deyoung and Harper 1948, Jones 1950a, The spanwise distribution of lift, Morton 1956, Nonweiler 1960, Harry and Trobaugh 1966, Loth and Boyle 1969, Hancock 1972, Mamada and Ando 1974, Sears 1974, Haftka 1977, Lundry 1977, Kida and Miyai 1978, Pao and Lan 1978, Deyoung 1979, Kuhlman 1979, Bera† 1980, Kida 1982, Hanin and Barsony-Nagy 1983, Marchman and Abtahi 1985, Wilmott 1986, Yeh and Plotkin 1986, Kuhlman and Liaw 1987, McCutchen 1989, Sears 1990, Smith and Kroo 1990.

Maximising the ratio of the two coefficients puts them equal to one another,

\[\frac{C_L^2}{\pi e A} = C_{D_0} \quad \Longrightarrow \quad C_L^{\ast} = \sqrt{\pi e A \, C_{D_0}} \tag{3}\]

Taking an Oswald efficiency of 0.90 and a zero-lift drag coefficient of 0.012, which are ordinary values for a clean sailplane and are assumed rather than measured,

\[A = \frac{b^2}{S} = \frac{(57.125)^2}{180} = 18.1 \tag{4}\] \[\left( \frac{L}{D} \right)_{max} = \frac{1}{2} \sqrt{\frac{\pi (0.90)(18.1)}{0.012}} = 32.7 \tag{5}\]

against a quoted 35, an agreement to within seven percent from geometry alone, and the lift coefficient at which it occurs is

\[C_L^{\ast} = \sqrt{\pi (0.90)(18.1)(0.012)} = 0.784 \tag{6}\]

The quoted numbers agree with the relation once each is paired with the correct weight. The best-glide speed is the speed at which the wing flies at $C_L^{\ast}$, with sea-level density $\rho = 0.0023769$ slug per cubic foot,

\[V_{bg} = \sqrt{\frac{2 (W/S)}{\rho \, C_L^{\ast}}}, \qquad V_{bg}\big|_{7.94} = \sqrt{\frac{2 (7.94)}{(0.0023769)(0.784)}} = 92.3 \, \text{ft/s} = 62.9 \, \text{mph}, \qquad V_{bg}\big|_{6.0} = 80.2 \, \text{ft/s} = 54.7 \, \text{mph} \tag{7}\]

At the 1,430 pound gross weight, a wing loading of 7.94 pounds per square foot, that is 62.9 miles per hour against a quoted 55.9, or 13 percent adrift. The same sources quote a wing loading of 6.0 pounds per square foot, which over 180 square feet is 1,080 pounds, well short of the gross weight. At that lighter weight the relation gives 54.7 miles per hour against the quoted 55.9, agreeing to two percent. The quoted performance therefore appears to be a one-pilot number, so the discrepancy at gross weight comes from pairing it with the wrong weight rather than from the aircraft.

The wing, and what a large aspect ratio buys and costs, falls within the induced-drag work already cited, and the sailplane literature on it includes Lippisch 1930, Turner 1942, Klemin and Walling 1943, Shenstone 1946, The Sailplane as 1948, Johnson 1949, Wiggi 1949, Yates 1949, Reussner 1950, Raspet 1952, Reussner 1953, Brown 1954, MacCready 1962, McMasters and Palmer 1975, Pierson 1977, Bennett 1978, McMasters 1979, Muser 1979, Pierson and Chen 1979, Minimum Altitude-Loss Soaring in, Pierson and Chen 1979b, Sliwa and Sliwa 1979, Turriziani 1979, Janzen and Precourt 1989, Hoey 1992, Allen 2006, Allen 2007a, Allen 2007b, Lin 2007. The design tradition this aircraft comes out of is set out in Thomas on sailplane design, and the drag bookkeeping behind the zero-lift term is Hoerner’s compendium.

Why This Aircraft Teaches Adverse Yaw

When an aeroplane rolls at rate $p$, a wing section at spanwise station $y$ meets the oncoming flow at an incidence changed by the local vertical velocity,

\[\Delta \alpha = \frac{p \, y}{V} \tag{8}\]

That changes the local lift, and through the polar above it changes the local induced drag, upward on the descending wing and downward on the ascending one. Integrating a spanwise load distribution to get a force is the oldest machinery in the subject, descending from lifting-line theory and the downwash it predicts, and the induced-drag papers under The One Relation develop it. Integrating the asymmetry across an elliptically loaded span gives the classical result,

\[C_{n_p} = -\frac{C_L}{8} \tag{9}\]

The minus sign is the crux. The wing that is rising carries more induced drag, so the aeroplane yaws away from the direction of roll.

The argument about teaching follows from the lift coefficient sitting in that numerator. The adverse yaw is proportional to $C_L$, and $C_L$ is inversely proportional to the square of the speed,

\[C_L = \frac{2 (W/S)}{\rho V^2} \tag{10}\]

so a slow aeroplane on a big wing produces a great deal of it. The relation between the induced yawing and rolling moments of a wing goes back to Munk 1925, the effect of the adverse yawing moment on lateral manoeuvrability at a high lift coefficient was measured in Fehlner 1942, and the period’s lateral control research is summarised in Weick and Jones 1937. The yawing moment due to rolling is treated in Johnson and Sternfield 1948 and Martina 1953, and the roll response it competes with is measured in Bennett and Johnson 1947 and set against roll control power in the landing approach in Hall and Boothe 1972. Further records appear in the survey clusters on lateral control, ailerons and adverse yaw and on lateral-directional stability, roll damping and coupling. The standard developments of the derivative machinery are Etkin and Reid on flight dynamics and, contemporary with the aircraft, Perkins and Hage. The account written for the pilots who would fly it is Hurt’s aerodynamics for naval aviators.

The Magnitude and the Rate

During a steady roll at helix angle $pb/2V$ the yawing moment coefficient is

\[C_n = C_{n_p} \cdot \frac{pb}{2V} \tag{11}\]

and the sideslip that moment drives against the aircraft’s directional stiffness is

\[\beta \approx \frac{|C_n|}{C_{n_\beta}} \tag{12}\]

The helix angle is a property of the configuration rather than of the flight condition, and that deserves a proof. In a steady roll the moment the ailerons apply and the damping moment the roll itself generates are in balance,

\[C_{l_{\delta_a}} \delta_a + C_{l_p} \frac{pb}{2V} = 0 \quad \Longrightarrow \quad \frac{pb}{2V} = -\frac{C_{l_{\delta_a}} \delta_a}{C_{l_p}} \tag{13}\]

There is no speed in that expression and no span either. The helix angle is fixed by the aileron power and the roll damping, both of which are shape properties, and both of which the period measured directly in tunnels and in flight, as in the roll-response papers of the previous subsection. The roll rate therefore follows,

\[p = \frac{pb}{2V} \cdot \frac{2V}{b} \tag{14}\]

and a long wing rolls slowly for the same reason a long lever turns slowly. Bank angle is the integral of that rate, so the time to reach a given attitude is

\[t = \frac{\phi}{p} = \frac{\phi \, b}{2 V \left( pb/2V \right)} \tag{15}\]

Taking the X-26A at 60 miles per hour and a generic jet trainer at 300, with every jet quantity assumed,

	X-26A	jet trainer, assumed
Wing loading, lb/ft²	7.9	60
Span, ft	57.1	25.3
Speed, mph	60	300
Lift coefficient	0.863	0.261
Sideslip developed, deg	6.2	1.4
Roll rate, deg/s	10.6	180
Time to 45 degrees of bank, s	4.25	0.25

The sailplane shows the student four and a half times as much sideslip and takes seventeen times as long to do it. The directional-stability side of that is set out in Price 1943 and Baker 1948, measured in flight in Crane and Reeder 1945 and examined for its sensitivity to the derivatives in Stengel 1980, and the coupled behaviour is treated in Davis 1957, Butler 1976a and Velger and Shinar 1983.

An Observability Index

Multiplying the two effects gives a rough index of how observable the phenomenon is, which comes out at seventy-five. Written as a scaling,

\[\beta \, t \propto \frac{(W/S) \, b}{V^3 C_{n_\beta}} \tag{16}\]

The helix angle cancels out of that expression, which is not obvious. It means the comparison does not depend on how powerful the ailerons are. Without the directional stiffness this scaling disagrees with the worked cases by exactly a factor of two, the ratio of the two aircraft’s assumed $C_{n_\beta}$, so the stiffness is an essential term and not a refinement.

How Slowly the Demonstration Could Be Flown

Adverse yaw grows as lift coefficient, so the demonstration wants to be flown as slowly as it safely can be, and what bounds that is the stall.

\[V_{stall} = \sqrt{\frac{2 (W/S)}{\rho \, C_{L_{max}}}} \tag{17}\]

This cannot be predicted, because the maximum lift coefficient is not known, and what a given section will reach is found by measurement, the approach the induced-drag and sailplane studies take. The relation is inverted instead. The quoted 46 mile per hour stall implies

\[C_{L_{max}} = \frac{2 (W/S)}{\rho V_{stall}^2} = 1.11 \tag{18}\]

at the light weight, or 1.47 at gross. The first is an ordinary value for an unflapped sailplane section and the second is high for one, so a third piece of evidence points to the lighter aircraft as the basis of the quoted performance figures, agreeing with what the glide speed already suggested.

Taking the light-weight value, the 60 mile per hour training case sits about thirty percent above the stall, which is close enough to make the phenomenon large and far enough to make it safe. At a fixed weight the sideslip scales as $C_L$ and therefore as $1/V^2$, so

\[\frac{V}{V_{stall}} = \frac{60}{46} = 1.30, \qquad \frac{\beta_{stall}}{\beta_{60}} = \left( \frac{60}{46} \right)^2 = 1.70 \tag{19}\]

Flown at the stall the sideslip would be about seventy percent larger, and unrecoverable inattention would cost rather more than a lesson.

Neither aircraft is more badly behaved than the other in any dimensionless sense. They are the same physics. In arithmetic form, the pedagogical argument is that the sailplane runs it slowly and at large amplitude.

Dependent Systems

Reading the Same Relation as a Power Requirement

Steady flight requires power to overcome drag,

\[P = \frac{W V}{L/D} \tag{20}\]

and a high lift-to-drag ratio means that this number is small. Taking an assumed 2,400 pound gross weight for the QT-2PC and an assumed lift-to-drag ratio of 20, degraded from the sailplane’s 35 by the engine, the shaft, the sensors and a fixed propeller,

\[P = \frac{(2400)(110 \, \text{ft/s})}{20} = 13{,}200 \, \text{ft lb/s} = 24 \, \text{hp} \tag{21}\]

Twenty-four horsepower of the hundred installed. That margin made the design possible.

Best Glide and Minimum Power

These are different speeds and the distinction matters here. The power-required curve and the two speeds it distinguishes are among the oldest results in aircraft performance and are treated thoroughly in the period literature, in Rice 1946, Hanks 1956, Bogdanovic et al. 1965, Finnestead and Antoniou 1965, Bert 1981, Laine 1982, Torenbeek and Wittenberg 1983, Hall and Rogan 1988, Hall and Rogan 1989. Writing the power required against speed shows two terms pulling opposite ways,

\[P = \tfrac{1}{2} \rho V^3 S \, C_{D_0} + \frac{2 W^2}{\rho V S \pi e A} \tag{22}\]

Differentiating and setting the derivative to zero puts the parasite term at three times the induced one, where maximising lift-to-drag put them equal. The consequences follow immediately,

\[C_{L, mp} = \sqrt{3} \, C_L^{\ast}, \qquad V_{mp} = \frac{V_{bg}}{3^{1/4}} = 0.760 \, V_{bg}, \qquad \left( \frac{L}{D} \right)_{mp} = \frac{\sqrt{3}}{2} \left( \frac{L}{D} \right)_{max} \tag{23}\]

so the power at the minimum is

\[\frac{P_{mp}}{P_{bg}} = \frac{0.760}{0.866} = 0.877 \tag{24}\]

a saving of 12.3 percent for flying 24 percent slower. For the QT-2PC on the assumed figures best glide is 81.5 miles per hour and minimum power is 62.0, and the quoted quiet cruise of 70 to 80 falls between them, as expected for an aircraft needing both endurance and a speed margin.

The noise value of that choice is almost nothing, and saying so keeps two motives from being confused. If radiated sound power followed shaft power, 12.3 percent would be worth

\[10 \log_{10} \frac{1}{0.877} = 0.57 \text{ dB} \tag{25}\]

Half a decibel. The loiter speed is explained by endurance and not by quiet. An engine asked for a fifth of its rating can be throttled deep, wrapped in mufflers that would strangle it at full power, and geared down to a large slow propeller. None of that is available to an aircraft that needs its engine. The silencing practice is documented in Ohta 1935, Nelson 1938, Czarnecki and Davis 1948, Davis et al. 1953, Stokes and Davis 1953, Tyler and Towle 1955, Dyer 1956, Fukuda 1960a, Fukuda 1960b, Keast 1961, Hukuda 1962, Fukuda 1963b, Fukuda 1963a, Emeric 1966, Alfredson 1971, Bender and Brammer 1973, Mutyala and Soedel 1974, Pegg and Hilton 1974, Bender and Brammer 1975, Robinson 1979, Shaikn 1979, Lux and Landwehr 1980, Hoffman and Kennedy 1982, Rhodes 1982, Prasad and Crocker 1983, Thomson 1983, Casey 1984, Matsushita and Suzuki 1984, Buchwalder 1985, Ferrari and Castelli 1985, Tanaka et al. 1985, Tarnow and Pommer 1988.

What Quiet Means, Quantitatively

This article uses decibels throughout and one should be defined before it does. Sound pressure level is a logarithmic ratio against a fixed reference,

\[\text{SPL} = 20 \log_{10} \frac{p}{p_{ref}}, \qquad p_{ref} = 20 \, \mu\text{Pa} \tag{26}\]

Intensity from a compact source falls over the surface of a sphere,

\[I = \frac{W_{ac}}{4 \pi r^2} \tag{27}\]

Intensity goes as the inverse square of range and pressure as the inverse first power, so the coefficient in front of the logarithm is twenty where an intensity ratio would give ten.

The level therefore falls with the logarithm of distance,

\[\text{SPL}(r) = \text{SPL}(r_0) - 20 \log_{10} \frac{r}{r_0} \tag{28}\]

Every doubling of slant range costs 6.02 decibels and no more. No number in the subject is more useful, and it sets what a design programme can hope to buy. Propagation in the lower atmosphere is reviewed in Nyborg and Mintzer 1955, atmospheric absorption is given in Bass et al. 1972 and updated in Bass et al. 1990, refraction and ground attenuation are treated in Kriebel 1972 and Rasmussen 1986, and the excess attenuation of aircraft noise with distance is measured in Wolf and Raspet 1986. The survey cluster on outdoor sound propagation and atmospheric absorption holds the remainder, and the physical principles behind it are Pierce on acoustics. The engineering practice of quieting machinery is Beranek on noise and vibration control.

The maximum range at which the aircraft is audible follows by setting the received level equal to the ambient,

\[r_{max} = r_0 \cdot 10^{\, (\text{SPL}(r_0) - L_{amb}) / 20} \tag{29}\]

Calibrating that against the record rather than assuming a source level, the QT-2PC was reported detectable at 750 feet, which against an assumed 40 dBA rural night ambient implies about 49.5 dBA at 250 feet. Sweeping the ambient,

Night ambient, dBA	Detected out to, ft
30	2,372
35	1,334
40	750
45	422

A detection range is a slant range and not an altitude, which reconciles two numbers the record gives separately. Flyover measurement is geometry before it is acoustics, and the conventions for relating source position, receiver position and measured level are established practice, in Zorumski 1977, Muller 1971, Chessell 1978, Willshire and Hilton 1979, Marsh 1981, Shivashankara and Stubbs 1987 and Peart 1991, and the clusters on aircraft noise sources, measurement, prediction and reduction and on outdoor sound propagation carry many more.

\[r = \sqrt{h^2 + x^2} \tag{30}\]

The aircraft was detectable at 750 feet and missions were flown no lower than 800. Those are the same statement. At any altitude above 750 feet the detection sphere does not reach the ground at all, so the 800 foot floor is the rule that the sphere must stay clear of the listener, with fifty feet of margin.

The aircraft’s usable altitude depends on how quiet the night is, as well as on the aircraft. From the range relation above, a change $\Delta L_{amb}$ in ambient scales the detection range by

\[\frac{r_{max}(L_{amb} - \Delta L_{amb})}{r_{max}(L_{amb})} = 10^{\Delta L_{amb}/20} = 10^{5/20} = 1.78 \tag{31}\]

so a five decibel change in ambient moves the detection range by 78 percent. The specification was always partly about the weather. Aural detection was studied in Schriever 1952, Bellucci 1963, Chew and Chapin 1963, Ollerhead 1971, Price and Hodge 1976, Ludeman 1979, Ramachandra 1979, Michel 1989, Mueller et al. 1993, Sheffield 2000.

Why the Simple Model Is the Right One

Atmospheric absorption is strongly frequency dependent and is negligible here. A slow propeller radiates at low frequency,

\[f = \frac{N_b \, \text{rpm}}{60} \tag{32}\]

which for four blades at 1,000 revolutions per minute is 67 hertz. How much sound the air absorbs, and how strongly that depends on frequency and humidity, is a measured subject with a long history, and the propagation work cited with the spreading law traces it. Absorption accumulates linearly with distance at a coefficient that rises steeply with frequency,

\[L_{abs} = \alpha \, r \tag{33}\]

Frequency, Hz	Coefficient, dB per 1,000 ft	Over 1,500 ft, dB
63	0.03	0.045
125	0.09	0.14
500	0.6	0.9
2,000	3.5	5.3

At 67 hertz the mission altitude costs under a tenth of a decibel, against the 6 that spreading alone costs per doubling. The coefficients are order-of-magnitude values for moderate humidity and are assumed. Spreading dominates, and the inverse-square model needs no apology.

The Propeller as the Lever

Propeller rotational noise rises sharply with tip speed,

\[V_{tip} = \frac{\pi D \, \text{rpm}}{60} \tag{34}\]

A conventional light aircraft propeller of 6 feet at 2,700 revolutions per minute reaches 848 feet per second. A large slow propeller of 8.5 feet at 1,000 reaches 445. The exponent relating sound power to tip speed depends on which harmonic dominates and on blade loading, and sources differ, so this article gives a range rather than a number.

Assumed exponent	Reduction, dB
5	14.0
6	16.8
7	19.6

The theory of how a turning blade radiates is Goldstein’s aeroacoustics, and the propeller performance it sits beside is McCormick.

There is a second reason the slow propeller is quiet. Propeller performance was reduced to charts in advance ratio and power coefficient long before it was computed, and those charts are what a designer choosing a diameter and a reduction ratio used, in the performance literature cited under best glide and minimum power. The noise that follows from the choice was a research subject by Deming 1937 and is reviewed in Regier and Hubbard 1953, small propeller aircraft are treated in Maglieri and Hubbard 1975 and a low noise propeller is designed and tested in Succi 1981, with the prediction theory in Farassat and Succi 1980 and Hanson 1983 and the tone’s growth with tip Mach number in Dittmar and Hall 1991. The propeller and rotor noise cluster below lists further work. The advance ratio compares forward speed to blade speed,

\[J = \frac{V}{n D} \tag{35}\]

and comes out at 0.65 for the conventional installation against 0.78 for the slow one, so the slow propeller’s blade sections are also more lightly loaded, which reduces the loading noise as well as the thickness noise the tip speed governs. Tip Mach number is

\[M_{tip} = \frac{V_{tip}}{a} \tag{36}\]

falling from 0.76 to 0.40 between the two installations.

Tens of decibels against the six that the 1,500 foot figure needed. The lever is far more than strong enough. The interesting question is then not how they made the propeller quiet but what was still audible once they had.

Why Quieting One Source Has a Ceiling

That the limit moves to the exhaust and the airframe is easy to assert, so it is shown here. Separating an aircraft’s total noise into its components, and then deciding which one to attack, is a discipline of its own, and the flyover-measurement papers listed with the detection-range table treat it. Independent sources add in power rather than in pressure,

\[L_{total} = 10 \log_{10} \sum_i 10^{L_i / 10} \tag{37}\]

So the gain from quieting one source is capped by whatever remains. Suppose the propeller starts ten decibels above everything else combined.

Propeller reduced by, dB	Total level, dB	Actual gain, dB
0	60.4	0.0
6	55.5	5.0
10	53.0	7.4
17	50.8	9.6
25	50.1	10.3

A seventeen decibel propeller reduction buys ten. Removing the propeller entirely would buy 10.4 and no more, because the floor is set by the other sources. Beyond about fifteen decibels of propeller work the total stops moving. The table puts a number on what would otherwise remain an intuition. Exhaust, airframe and transmission noise all become the limit as soon as the propeller stops dominating.

What It Gave Up to Carry an Engine

The X-26A glides at 35 to 1. The QT-2PC carries an engine, a shaft, a propeller, fuel, sensors and a second crewman on the same wing, and on the assumed figures its glide falls to 20 to 1 at a weight 1.7 times greater. Sink rate is power divided by weight, or equivalently speed divided by glide ratio,

\[V_{sink} = \frac{P}{W} = \frac{V}{L/D} \tag{38}\]

Written that way it supplies a second and independent check on the polar. Minimum sink is the minimum-power condition derived above, not the best-glide one.

Evaluating at the minimum-power point and the light weight, with the best-glide speed of 54.7 miles per hour and the lift-to-drag ratio of 32.7 found above,

\[V_{mp} = 0.760 \times 54.7 = 41.6 \, \text{mph} = 61.0 \, \text{ft/s}, \qquad V_{sink} = \frac{61.0}{(0.866)(32.7)} = 2.16 \, \text{ft/s} = 129 \, \text{ft/min} \tag{39}\]

which is 129 feet per minute at 42 miles per hour, against a quoted 124 at 46. That is 4 percent in sink rate and 10 percent in speed, from the same two assumed parameters that produced the glide ratio and without any further fitting. The glide ratio and the minimum sink are independent quoted numbers, so reproducing both from one polar is worth more than reproducing either alone.

It is still a sailplane. Even loaded and draggy it would descend at a few hundred feet a minute with the engine stopped, so the crew could in principle shut down and loiter in silence. The glide performance behind it is Lundberg 1937, Lundberg 1938, Jackson et al. 1993, Colling 1995.

The Sensors and the Mission

The observation equipment, the low-light television and the night-vision devices of the period are Cornell Aeronautical Lab INC Buffalo NY 1971b, Cornell Aeronautical Lab INC Buffalo NY 1971c, Cornell Aeronautical Lab INC Buffalo NY 1971a, Bailey and McClintic 1974, Reising et al. 1996, Craig et al. 1999, Pleban and Beal 2002, Fischer 2006. This article does not dimension them, because the acoustic and aerodynamic questions are the ones the airframe answers and the sensors were carried rather than enabled by it.

The Flight Test Record

The two halves of this designation have unequal records.

The X-26A flew at the Naval Test Pilot School from the late 1960s and remained in the syllabus for decades, and the Navy’s product page still lists it as operational, with two in the inventory. Its record is a curriculum rather than a test report, and the teaching tradition it sits in is described for the Naval Test Pilot School in Johnson 1975 and for the Air Force school in Eppley 1963, with the flying-qualities course text in Air Force Test Pilot School Edwards Afb Ca 1991c, the pilot rating scale in Cooper and Harper 1969, the specification of the period in Chalk and Wilson 1969 and its lateral-directional requirements in Ashkenas 1965b, and the history of the subject in Ashkenas 1984 and Mitchell et al. 2003. Teaching flight testing through soaring is described in Stewart 2016. Related work is listed under the flying and handling qualities and flight test clusters.

The QT-2PC record is short, specific and much better documented as history. In Polmar’s account in Naval History, two aircraft reached the Army airfield at Soc Trang in the Mekong Delta on 22 January 1968 and began operations almost immediately, flying 591 hours of night surveillance between 24 January and 24 March 1968 under the Prize Crew evaluation. In Albertson’s account in Army Aviation, repeated passes over the airfield at decreasing altitude found the aircraft first heard at 750 feet, against the 1,500 of the later YO-3A specification, so missions were flown no lower than 800 feet and en route altitudes were generally 1,200 to 1,500.

Measured against that 1,500 foot figure the aircraft fell 6 decibels short, one doubling of distance. For a first article the shortfall is small, and the Army awarded Lockheed a YO-3A production contract in July 1968 on the strength of it. The two aircraft returned to the Test Pilot School in 1969 and were redesignated X-26B. Lockheed carried the work forward through the Q-Star to the YO-3A. The YO-3A’s numbers and dates differ between accounts. The X-26 summary gives eleven pre-production aircraft operating in Southeast Asia from mid-1969 to late 1971, the YO-3A summary gives eleven built, nine of which operated in South Vietnam from late June 1970 to September 1971, and Polmar gives fourteen ordered, thirteen of them shipped to Vietnam in early 1970. The range all three support is operation in Vietnam during 1970 and 1971.

Seven research records cited here name a Schweizer aircraft, the Q-Star or the YO-3A in their titles, and the only one that evaluates the YO-3A in its operational role is the Army’s preliminary evaluation, in Condon et al. 1970. The others are described under The Source Base. No cited record concerns the QT-2PC itself.

Comparison With Ground Prediction

Two predictions can be checked against the record and they fare differently.

The glide performance check succeeds and is not impressive. The prediction of 32.7 falls seven percent short of the quoted 35 using an assumed drag coefficient and an assumed span efficiency, and a model with two free parameters that lands within seven percent has demonstrated very little. It is reported because it is a consistency check on the geometry, not because it is evidence.

The reconciliation of the quoted glide speed carries more weight. The best-glide speed relation under The One Relation and the quoted 55.9 miles per hour disagree by 13 percent at gross weight and agree to two percent at the one-pilot weight. Here the model and the sources are both right and the conflict lies only in pairing a speed with the wrong weight. Of the two checks it is the more useful, because it resolved an apparent conflict rather than confirming an expected agreement.

The acoustic prediction cannot be checked at all. The source level was calibrated backwards out of the one reported detection distance, so the detection-range table reproduces that distance by construction and not by prediction. It has no independent confirmation. What it does provide is the sensitivity, and the sensitivity is the finding. The detection range moves 78 percent for a 5 decibel change in ambient, by the range ratio under What Quiet Means, so the aircraft’s usable altitude was never a property of the aircraft alone.

What the Data Changed

The X-26A changed how test pilots are taught and nothing else, a change of consequence. Generations of graduates were shown adverse yaw in a slow sailplane instead of a jet, although the type was not harmless, and two of its crashes, in 1971 and 1972, killed their pilots. The profession gained from it and aeronautics did not, and no aerodynamic result records it.

The X-26B changed a good deal more. The QT-2PC demonstrated that a manned aircraft could loiter low at night without being heard, and it came within 6 decibels of the demanding 1,500 foot figure later specified for the YO-3A on the first attempt. It led directly to the Q-Star and the YO-3A, and the YO-3A flew operationally.

The deeper consequence is that the quiet-aircraft problem turned out to be an acoustics problem and not an aeronautics problem. Once the propeller was slowed, the arithmetic under Why Quieting One Source Has a Ceiling moves the limit to the exhaust, the airframe and the transmission. That is the signature of a design that has run out of dominant terms.

The Contemporary Literature

Cluster	Records
Propeller aerodynamics, design and propulsion	279
Propeller and rotor noise	249
Aircraft noise sources, measurement, prediction and reduction	242
Performance, power required, endurance and range	235
Aeroelasticity, flutter and gust loads	207
Flight test, system identification and parameter estimation	204
Pilot training, simulation, human factors and safety	189
Lateral control, ailerons and adverse yaw	181
Sailplanes, gliders and soaring	178
Outdoor sound propagation and atmospheric absorption	165
Flying and handling qualities	161
Lateral-directional stability, roll damping and coupling	158
Community noise, annoyance and psychoacoustics	146
Induced drag, span loading and the high aspect ratio wing	146
Acoustic and aural detection of aircraft	138
Unmanned aircraft design and operation	111
Engine exhaust noise and mufflers	86
Loss of control, upset recovery, stall and spin	80
Flight control, control allocation and fault tolerance	77
Aerodynamics, airfoils and aerodynamic design	68
Airframe noise, cabin noise and vibration	63
Surveillance, reconnaissance and observation	56
Electric, hybrid-electric and solar-powered aircraft	47
Flight dynamics, stability and simulation models	35
Other aeronautical literature	30
Wind tunnels, models and test technique	26
Rotorcraft and vertical lift flight mechanics	19
Total	3,576

Both halves of this designation have living descendants, and there is a pattern in what happened to them.

Each programme existed because of a human in the aircraft, and in each case the modern answer removed the human. The X-26A existed to teach a pilot to notice something. The X-26B existed to make a manned aircraft inaudible. One mission is now largely discharged by systems that make noticing unnecessary, and the other by aircraft with nobody aboard that are quiet because they are small.

The X-26A’s Argument Became a Regulation

This is the largest thing that has happened to the first half of the X-26, a considerable promotion for a claim that no source found here ever measured.

Loss of control in flight is now a named accident category, and it was the largest fatal accident category for jet transports worldwide from 2001 through 2010. Upset prevention and recovery training became a regulatory requirement and no longer a good idea, and the surrounding literature covers startle and surprise in Landman et al. 2017, Landman et al. 2020 and Causse et al. 2026, upset recovery training and its simulators in Degtyarev et al. 2021, Ryffel et al. 2019 and Wu et al. 2020b, the degradation of manual flying skill under automation in Leonidov 2025, a loss of control accident in Bromfield et al. 2023a, and the envelope protection and automatic recovery that make noticing unnecessary in Lombaerts et al. 2017 and Wang et al. 2024a. The clusters on loss of control, upset recovery, stall and spin and on pilot training extend the list.

The X-26A’s justification was that a pilot must meet the phenomenon somewhere safe before meeting it somewhere dangerous. That was an assertion in the 1960s and it is now a rule for airline pilots.

The other half of the answer removes the need to notice at all. Envelope protection in a fly-by-wire aircraft prevents the excursion instead of training the recovery, a different philosophy and one in tension with the first. An aircraft that cannot be upset does not teach its pilot what an upset feels like, and the training requirement exists partly because of that.

Adverse Yaw, Identified From Data

The derivatives the X-26A demonstrated by feel are now extracted numerically from flight data, and the lateral-directional behaviour is modelled, damped and allocated across control surfaces instead of flown around, in Zhu and Duan 2015, Korsun et al. 2018, Kumar and Ghosh 2018, Dhayalan et al. 2018, Wu et al. 2018, Ma et al. 2019, Shen et al. 2021, Lyu et al. 2022, Wang et al. 2022b, Jategaonkar 2023, Korsun and Moung Htang 2023, Kumar and Ghosh 2023b, Shi et al. 2023a, Simmons et al. 2023b, Sánchez et al. 2024, Abdul Rashid et al. 2025.

Quiet Flight, Attempted Again

Electric propulsion has revived the quiet aircraft as a serious objective, this time for community acceptability rather than concealment, and that has turned the subject from a physical one into a partly perceptual one. Psychoacoustic annoyance metrics and community response are where the effort now goes, in Gille et al. 2017, Christian 2021, Boucher et al. 2023 and Tracy et al. 2024, together with the acoustic design of electric and distributed-propulsion aircraft in Nark et al. 2017, Berton and Nark 2019 and Thomas and Hansman 2021, design for community noise in Iemma 2016 and Sahai et al. 2017, and the urban air mobility case in Rizzi and Rafaelof 2021. Both strands continue in the clusters on community noise, annoyance and psychoacoustics and on aircraft noise sources.

The QT-2 wanted to be inaudible to an enemy, and contemporary quiet-aircraft work wants to be acceptable to a neighbour. The physics is identical and the criterion is not. Spherical spreading still costs 6 decibels per doubling. What has changed is that the threshold is no longer an ambient noise level and a listening sentry, but a population and its tolerance.

The Mission Went Unmanned and Solved the Acoustic Problem by Accident

The QT-2PC’s difficulty was that a manned aircraft has to be big enough to carry a person. That set the wing area, the weight, the power and therefore the noise, and every gram of muffler and every foot of extension shaft was spent fighting a floor set by human size.

A small unmanned aircraft has no such floor. Persistent low-altitude observation is now routine, and the aircraft that fly it are quiet not because anyone silenced them but because they are small and need very little power, in Stewart et al. 2012, Leahy et al. 2015, Sonmez and Alemdaroglu 2015, Abich et al. 2016, Frazier 2016, Hosseini and Mesbahi 2016, Kisabo et al. 2017, Hasan et al. 2018, Huang et al. 2018, Shin et al. 2018, Olsen et al. 2019, Wu et al. 2019a, Dinc and Otkur 2020, Chu et al. 2021, Januszewska and Pringle 2021, Monzambe et al. 2024, Setiawan et al. 2026.

The programme’s constraint turned out to be the thing that could be deleted, which is also how the X-25 question, how to give a descending crewman a choice, was answered.

And Now Everyone Wants to Hear the Aircraft

The QT-2’s problem has been inverted. Contemporary work is largely about detecting small aircraft acoustically, the same physics read from the other end, in Brown et al. 2016, Culver 2016, Goldman 2016, Kim 2016, Bernardini et al. 2017, Kloet et al. 2017, Harvey and O’Young 2018, Oleynikov et al. 2018, Sedunov et al. 2018, Guzik et al. 2019, Haddad et al. 2019, Sedunov et al. 2019, Manickam et al. 2020, Kozak 2021, Liu et al. 2021, Uddin et al. 2021, Aydın and Kızılay 2022, Gopalan et al. 2022, Kadyrov et al. 2022, Rasband et al. 2023, Sahithi 2023, Seidaliyeva et al. 2023, Dafrallah and Akhloufi 2024, Kumar S Rajanikanth 2024, Paszkowski et al. 2024, Hai et al. 2025, Jekateryńczuk and Piotrowski 2025, Lotinga et al. 2025c, de Macedo et al. 2025, Alimadadi 2026, Ghenescu et al. 2026, Sesham et al. 2026.

Propeller Noise, Computed

Propeller and rotor acoustics is now a computational discipline, with a benchmark in Casalino et al. 2021, parametric and wake studies in Yang et al. 2017 and Kingan and Parry 2020, positive and negative thrust in Goyal et al. 2024, adjoint design in Zhi et al. 2025 and prediction methods compared with flyover data in Domogalla et al. 2026, and outdoor propagation likewise, in Wilson 2024, Ostashev and Wilson 2022, Kirby 2021b and Hart et al. 2016. The two corresponding clusters, propeller and rotor noise and outdoor sound propagation, hold more of this work.

The Very Efficient Aeroplane

High aspect ratio has become a mainstream objective rather than a sailplane peculiarity, in the transport studies Kretov and Tiniakov 2022, Ma et al. 2022a, Wahler et al. 2025a and Gilbrook et al. 2025 and the high-altitude aircraft of Fladeland et al. 2019 and Doyle 2020, while the sailplane itself is still being refined, in Aero Structural Optimization 2018 and Yu 2026. The induced drag and aeroelasticity clusters below continue the record.

Training Transfer and Simulator Fidelity

The X-26A’s justification was a pedagogical assertion, and no measurement of it was found here. Contemporary work on training transfer and simulator fidelity is where that assertion would now have to be defended, in Harnyoot 2018, Myers et al. 2018, Henriquez Huecas et al. 2022, Hjellvik and Mallam 2024, Zhang et al. 2025b, Somerville et al. 2026a, Somerville et al. 2026b.

What the Survey Shows

The X-26A and the X-26B were both about a human in the aircraft, and modern practice answers each by removing the human. Adverse yaw is still taught in slow aircraft, but envelope protection now prevents the excursion instead of teaching the recovery, so the X-26A’s method is one answer among several. The X-26B’s mission is flown by unmanned aircraft that are quiet because they are small, and the same acoustic equations are now used more often by the listener than by the flyer.

The survey also shows an absence. Nothing found here measures whether flying a sailplane teaches adverse yaw better than a simulator or a briefing does. The X-26A’s central claim remains untested sixty years on, which is a curious position for an argument that has meanwhile been written into regulation.

Propeller aerodynamics, design and propulsion

Propeller aerodynamics, design, efficiency and structure, with the engines and propulsion systems that drive them. 86 of the 279 records date from before 1970.

279 records. [Adamson 1968] [Adler 1960] [Aerodynamic Design of Low-Speed 1986] [Aithal et al. 2004] [Aleshin et al. 2018] [Alfares 2026] [de Almeida et al. 2016] [Alonso Castilla et al. 2021] [Altman 2002] [Annand 1950] [Army Service Forces Washington Dc 1940] [Avco Lycoming Div Stratford Ct 1970] [Avrenli and Dempsey 2015] [Baek et al. 2015] [Baek et al. 2021] [Baker 1942] [Ball 1987] [Balyakin 2015] [Barufaldi and Morales 2023] [Baxter 1951] [Beauregard 1964] [Bell Aerospace Co Buffalo Ny 1956a] [Bell Aerospace Co Buffalo Ny 1956b] [Bell Aerospace Co Buffalo Ny 1956c] [Berenschot 2001] [Bergman 1971] [Bergmann et al. 2021] [Bert 1999] [Beschorner et al. 2025] [Bhat et al. 2026] [Bienen 1927] [Biermann and Conway 1942] [Bogdanovic et al. 1965] [Borer et al. 2016] [Boswell and Miller 1968] [Heldenbrand et al. 1975] [Hu and Booker 2022] [Legrand et al. 2025] [Litherland et al] [Bravo et al. 2021] [Briardy and Head 1968] [Bridges 2021] [Brockett 1972] [Bronz 2019] [Brun et al. 1947] [Burnell and Fan 1957] [Butler et al. 1966] [Robb et al] [Calise et al. 1999] [Campbell and McDonald 1963] [Cao et al. 2026] [Capone and Bare 1987] [Meyer and Johnson 1952] [Carroll and Carroll 2005] [Cavcar 2011] [Cavcar and Cavcar 2005] [Chakraborty and Mishra 2023] [Chang and Sullivan 1984] [Chapter 12 Converting 2019] [Chen et al. 2026a] [Chen et al. 2026b] [Cheng et al. 2022] [Cheng et al. 2023] [Clark 1953] [Codon and Bowles 1979] [Colozza 2002] [Composite Propeller Blade 1972] [Computer Simulates Aircraft-Engine Performance 1974] [Computer Techniques for Propeller 1976] [Cook 1965] [Coward 1955] [Cummings 1929] [Cummings 1968] [Cusati et al. 2023] [Dahms and Bardenhagen 2019] [Dailey 1955] [De Hoff and Hall 1978] [de Vries and Vos 2023] [de Vries et al. 2019] [Deng et al. 2026] [Denning 1962] [Design and Analysis 2023, Design and Analysis of Propeller] [Deveaux 1965] [Dinc and Otkur 2020] [Doblhoff 1956] [Dorfling and Rokhsaz 2015] [Dryden and Ballif 1930] [Duffy 1968] [Duhl and Thompson 1977] [Dunlap 1969] [Durand 1893] [Echavarria and Poroseva 2015] [Glodeck and Standahar 1944] [Epstein and O’Flarity 2019] [Erickson et al. 1965] [Eyerci̇oğlu and Aladağ 2021] [Fard et al. 2022] [Farokhi and Vertzberger 1989] [Felder et al. 2009] [Finger et al. 2020a] [Fredericks et al. 2013] [Friedrich and Robertson 2015] [Fry 1967] [Gao et al. 2019] [Gao et al. 2024b] [Gayle and Jeracki 1989] [General Electric Co Cincinnati Oh 1964] [Gerstle et al. 1999] [Gilyard 1974] [Goland et al. 1964] [Swick and Skarvan 1967] [Zilliac 2026] [Gulyaeva et al. 2018] [Gur 2014] [Harris 1996] [Heidelberg and Woodward 1989] [Hennessy 2014] [Hiller Aircraft Corp Palo Alto Ca 1956] [Hirschkron et al. 1979a] [Hirschkron et al. 1979b] [Hirschkron et al. 1979c] [Hirsh 1965] [Hoehne and Hoffman 1961] [Hoyos et al. 2021] [Huang 2023] [Hughes and Gazzaniga 1988] [Tupitsyin 2023] [Jamison 1966] [Jeracki and Mitchell 1981] [Jones 1965] [Jones et al. 2013] [Kim et al. 2026] [Koch 1998] [Korsun et al. 2017] [Korsun et al. 2024] [Kozakiewicz and Grzegorczyk 2021] [Kriebel 1964] [Kruger and Uranga 2024] [Köhler and Jeschke 2021] [Laitone 1983] [Large and Pesyridis 2018] [Lee and Ko 2025] [Lee and Yee 2024] [Lee et al. 2022a] [Leishman 1966] [Hang et al. 2022] [Level Flight Performance Flight 2003] [Li and Da Ronch 2025] [Li et al. 2022c] [Li et al. 2026] [Lieberman and Hoffman 1964] [Liu et al. 1983] [Louis and Louis 2020] [Lourenco et al. 1996] [Lucas 1978] [Ma et al. 2020] [Ma et al. 2025] [Macey 1956] [MacNeill and Verstraete 2017] [Madureira and de Almeida 2026] [Magee and Taylor 1971b] [Malina and Parsons 1941] [Mangold and Strohmayer 2025] [Maynard and Evans 1945] [McCormick 1956] [McVeigh and McHugh 1984] [Meng et al. 2017] [Merrill 2003] [Meyerhoff and Zvengrowski 1962] [Mikkelson et al. 1984] [Mitchell and Mikkelson 1982] [Morgado et al. 2013] [Morgan 1954] [Morgan 1961] [Nakka and Alexander-Ramos 2021] [Naval Air Test Center Patuxent River MD 1957] [Nelson 1965] [Newell and Herrick 1979] [Nimal and Venkatesan 2019] [Norris and Bauer 1993] [Omair Alhatim 2026] [Orme et al. 1998] [Ormsbee 1977] [Ormsbee et al. 1977] [Park et al. 2018b] [Park et al. 2023] [Performance Characteristics of Two-Blade 1930] [Perisho 1959] [Perry et al. 2021] [Perry et al. 2023] [Petrovskii 1965] [Phillips 2002] [Picolet 1932] [Pieper 1965] [PlCKERELL and Cresswell 1968] [Plunkett 1949] [Povinelli 2002] [Propeller Performance 2012] [Propeller Propulsion Systems 2010] [Propeller System for Bush 1999] [Przedpelski 1965] [Qin et al. 2023] [Quillet et al. 2023] [Randall 1955] [Reader 1980] [Reuter 1939] [Rezy et al. 1979] [Roberts 1964] [Rocket Effect in Standard 1937] [Rodger Dyson] [Rogers and Fasciano 2016] [Rose and Jeracki 1989] [Rostami 2024] [Saari and Wallner 1946] [Saraçyakupoğlu et al. 2022] [Sarup 2025] [Sarup 2026] [Satria Palar et al. 2024] [Scholz 2021] [Schrenk 1932] [Schwartz et al. 1986] [Scoppe 1973] [Shan et al. 2025] [Shang et al. 2025] [Shao et al. 2025] [Shi et al. 2024] [Showers 1952] [Siddavatam et al. 2024] [Simizu 1944] [Simmonds 1967c] [Simmonds 1967a] [Simmonds 1967b] [Simmons et al. 2023a] [Sinacori and Lange 1961] [Stresses in a Rotating 1938] [Stuart 1943] [Sziroczak et al. 2020] [Søntvedt 1974] [Teixeira and Cesnik 2019] [Theodorsen 1960b] [Theodorsen 1960a] [Theodorsen and Nomicos 1961] [Traub 2016a] [Traub 2017] [Tucker 1999] [Use of Reinforced Plastics 1974] [Usov et al. 2026] [Valentine and Kader 1976] [Van et al. 2019] [Vance 1991] [Venkatesh et al. 2025] [Vepa 2018] [Vepa 2020] [Vlasov and Ovdienko 2020] [Vollo and Brassaw 1956] [Waddington et al. 2023] [Wallner and Sorin 1946] [Walz 1976] [Walz 1978] [Wang et al. 2026b] [Webb and Willer 1952] [Wells 1977] [Weng et al. 2021] [Wheeler et al. 2021] [Whitmore and Merrill 2012] [Worobel and Peracchio 1968] [Wu and Mora-Camino 2012] [Wu et al. 2023b] [Xiao et al. 2024] [Xie and Haberland 1999] [Xie et al. 2023a] [Yang et al. 2023] [Yildiz 2022] [Yost 1976] [Zabinsky and Laszewski 1956] [Zhang et al. 2018b] [Zhang et al. 2023c] [Zhao et al. 2023a] [Zola et al. 1978]

Propeller and rotor noise

Tone, broadband and interaction noise of propellers, rotors and fans, by theory, computation, wind tunnel and flight measurement.

249 records. [Moshkov et al. 2018] [Afari and Mankbadi 2024] [Akila et al. 2018] [Alì et al. 2026] [Amargianitakis et al. 2021] [Amiet 1988] [Ingraham n.d.] [Lee and Lee 2023] [Patterson et al] [Arndt and Borgman 1971] [Austin D. Thai et al] [Barton and Mixson 1981] [Berton and Nark 2019] [Bewick et al. 2001] [Bhardwaj et al. 2026] [Block 1986] [Block and Gentry 1986] [Bonomo et al. 2024] [Borchers 2009] [Brooks and Mackall 1984] [Brungart et al. 2019] [Bullmore et al. 1990] [Byrd and Cates 1977] [Cantos et al. 2026] [Casagrande Hirono et al. 2023] [Casalino et al. 2021] [Catherines and Mayes 1975] [Chanaud 1972] [Chapman 1988] [Feiler et al. 1972] [Chen et al. 2023] [Chusseau et al. 2024] [Chyla 2024] [Corbishley et al. 2026] [Hawkings and Lowson 1974] [Dahan et al. 1980] [Deming 1937] [Deming 1940] [Dittmar 1977] [Dittmar 1978] [Dittmar 1981] [Dittmar 1984] [Dittmar 1985] [Dittmar 1989a] [Dittmar 1989b] [Dittmar and Hall 1991] [Dittmar and Jeracki 1981a] [Dittmar and Jeracki 1981b] [Dittmar and Stang 1987a] [Dittmar and Stang 1987b] [Dittmar and Stefko 1983] [Dittmar et al. 1979] [Dittmar et al. 1982] [Dittmar et al. 1983] [Dobrzynski 1993] [Domogalla et al. 2026] [Hanson and Parzych 1993] [Dunn and Farassat 1990] [Dunn and Farassat 1992] [Dunn and Tarkenton 1989] [Dunn et al. 2015] [Elliot et al. 1990] [Elliott et al. 1989] [Envia 1992] [Ernsthausen 1937] [Evans and Dunbar 1982] [Eversman 1990] [Farassat and Succi 1980] [Fink 1978] [Fruncillo et al. 2024] [Fruncillo et al. 2025] [Fuller and Jones 1987] [Gandhi et al. 2022] [Gautam et al. 2025] [Gedney et al. 1998] [Glegg and Devenport 2024] [Goyal et al. 2024] [Goyal et al. 2025] [Greenwood and Schmitz 2014] [Guo and Thomas 2015] [Guérin et al. 2023] [Gwak and Lee 2017] [Halimi et al. 2019] [Hambrey et al. 2017] [Hanson 1976] [Hanson 1983] [Hanson 1985] [Hanson 1986] [Hanson and Fink 1978] [Hanson and Fink 1979] [Hanson and Magliozzi 1985] [Hanson et al. 2023] [Hasegawa and Sakaue 2023] [Hasegawa and Sakaue 2024] [Healy 1969] [Hodgson and Guo 2006] [Huang et al. 2016] [Huang et al. 2020] [Huang et al. 2023b] [Huang et al. 2025] [Iemma et al. 2021] [Ingraham 2023] [Ingraham et al. 2019] [Içke and Baysal 2021] [Jeong et al. 2023] [Jia and Lee 2021] [Johnston and Donham 1982] [Jung et al. 2025b] [Kallergis 1987] [Karimian et al. 2023a] [Karimian et al. 2023b] [Kato et al. 2018] [Keshavan 1980] [Kim et al. 2025c] [Kingan and Parry 2020] [Kingan and Self 2009] [Kordan et al. 1985] [Kotwicz Herniczek] [Lee et al. 2025] [Lester and Fuller 1986] [Leth et al. 1998] [Li et al. 2023b] [Light Aircraft Propeller 1993] [Loewy and Sutton 1966] [LØVik and Holden 2024] [Ma and Guo 2018] [Maglieri and Hubbard 1975] [Magliozzi 1982] [Magliozzi 1983] [Malgoezar et al. 2019] [Marinus et al. 2009] [Marques et al. 2026] [McCurdy 1985] [McCurdy 1989] [McCurdy 1991] [McCurdy and Powell 1984] [McKay and Kingan 2019] [Merino-Martinez and Nicola Quaroni 2025] [Metzger 1981] [Metzger and Farassat 2007] [Metzger et al. 1976] [Metzger et al. 1980] [Miller et al. 1982] [Misol 2020] [Mixson and Powell 1984] [Mixson and Powell 1985] [Mixson et al. 1979] [Mixson et al. 1981] [Morhy Cavalcante et al. 2026] [Moshkov 2022] [Moshkov 2026a] [Moshkov 2026b] [Moshkov 2026c] [Moshkov and Samokhin 2016] [Moshkov and Samokhin 2021] [Moshkov and Yakovlev 2023] [Moshkov et al. 2019] [Nallasamy et al. 1987] [Nallasamy et al. 1989] [Nark et al. 2004] [Nark et al. 2017] [Sun et al. 2023c] [Vazquez Casique et al. 2024] [Wiedemann et al. 2022] [Zawodny et al. 2025] [Noda et al. 2022] [Noda et al. 2025] [Oleson and Patrick 1998] [Optimization Software Helps Design 2000] [Palchikovskiy et al. 2023] [Palleja-Cabre et al. 2024] [Park 2026b] [Parry 1995] [Parry and Crighton 1989] [Pascioni et al. 2026] [Paswan et al. 2025] [Patrick 1986] [Patrick and Nagel 1989] [Pereira Gouveia da Silva et al. 2025] [Peterson and Warmbrodt 1996] [Pla et al. 1989] [Pogosyan and Moshkov 2023] [Polacsek et al. 2000] [Pope et al. 1987a] [Pope et al. 1987b] [Qin and Huang 2024] [Quaroni et al. 2024] [Ragani Lamouki et al. 2026] [Raisbeck and Mills 1987] [Rathgeber and Sipes 1977] [Reduced Noise in Interiors 1988] [Regier and Hubbard 1953] [Rennison et al. 1980] [Revell et al. 1980a] [Revell et al. 1980b] [Revell et al. 1982a] [Revell et al. 1982b] [Roger et al. 2022] [Ruijgrok 1980] [Runyan 1980] [Ruotolo 1999] [Madhusudhana et al. 2024] [Salikuddin and Ahuja 1989] [Salikuddin et al. 1990] [Santos et al. 2023] [Sasaki et al. 2012] [Schaeffer and Sternfeld 1978] [Shao et al. 2026] [Shreve 1977] [Simon et al. 2023] [Spencer et al. 1969] [Sree 2015] [Stabeli Diehl et al. 2025] [Succi 1981] [Succi et al. 1983] [Sun et al. 2023a] [Федорович et al. 2021] [Trascinelli et al. 2026] [Trillo 1966] [Tsouka 2024] [Unruh 1987] [Unruh 1988b] [Unruh 1988a] [Unruh 1989] [Van Deventer 1979] [Van Treuren and Wisniewski 2019] [Wang and Zhong 2025] [Wang et al. 2024b] [Widnall and Wolf 1980] [Wilby and Wilby 1989] [Wilby et al. 1980] [Woan and Gregorek 1978] [Woodward 1987a] [Woodward 1987b] [Woodward and Loeffler 1991] [Wright and Lee 1984] [Wu et al. 2023a] [Xue et al. 2023] [Yang et al. 2017] [Yang et al. 2026] [Yin and Stuermer 2013] [Yuen 2026] [Zaman et al. 2024] [Zhang et al. 2023a] [Zheng et al. 2023] [Zhi et al. 2025] [Zhong et al. 2023] [Çelebi et al. 2025] [Šulc et al. 1982]

Aircraft noise sources, measurement, prediction and reduction

Aircraft noise in general, its measurement, monitoring, prediction tools and reduction programmes, where a title names no single source.

242 records. [A Review 2011] [Acoustic Field Separation 2023] [Action against Aircraft Noise 1989] [Aircraft Flyover Noise Measurements 1976] [Aircraft Noise Assessment 1980] [Aircraft Noise 2012a] [Aircraft Noise 1969] [Aircraft Noise 2012b] [Aircraft Noise Prediction 1989] [Aircraft Noise Sources 1989] [Akatsuka 2024] [Ali 1989] [Allanach et al. 2010] [An Algorithm for Microphone 2026] [An et al. 2025] [Ang and Cui 2022] [Arcondoulis and Liu 2019] [Asakura and Takagi 2020] [Aujogue] [Avallone et al. 2018] [Badgley and Laskin 1970] [Barlow et al. 1972] [Barstow 1940] [Barstow 1941] [Berry and Harris 2024] [Berry and Speakman 1993] [Bertsch et al. 2010] [Bertsch et al. 2019] [Bertsch et al. 2023] [Bohn and Shovlin 1981] [Bossler and Smith 1974] [Boston et al. 1984] [Bowles et al. 1974] [Brear et al. 2003] [Brown et al. 1969] [Brusniak et al. 2019] [Bryson et al. 2016] [Bui et al. 2021] [Caillet et al. 2026] [Campanella 1976] [Certified Aircraft Noise Data 2012] [Charly KONE et al. 2025] [Cheeseman 1975] [Chen et al. 2015b] [Chen et al. 2021] [Chopra 2002] [Ciaburro et al. 2020] [Clark 1981] [Cochrane and Boissevain 1978] [Cochrane and Carros 1975] [Cochrane et al. 1981] [Cochrane et al. 1982] [Coen and Richwine 2017] [Cole and England 1967] [Conners et al. 2005] [Connor et al. 1975] [Cross 1984] [Cross and Watts 1983] [Culver 2016] [Cuppoletti et al. 2024] [Development of a New 1976] [Dittmar 1983] [Dolmans and Patrick 1998] [Domogalla et al. 2021] [Durbin 1983] [Eisenhut and Strohmayer 2026] [Envia 2018] [Eppel 1981] [Ffowcs Williams and Hawkings 1969] [Fidell et al. 1989a] [Fleming 1954] [Ford 1990] [Ford CEng MRAeS 1992] [Frampton et al. 1993] [Friedlander et al. 2018] [Fujita et al. 2021] [Gasaway 1969] [Gasaway and Hatfield 1963] [Geiger 2002] [Gennaretti et al. 2017] [Gibbs 2023] [Griffith 1971] [Griffith and Roberts 1972] [Nakayama et al. 2025] [Santos et al. 2025] [Hai et al. 2025] [Hargest 1966] [Harlamert 1974] [Henke et al. 2010] [Hille et al. 2023] [Hilton and Henderson 1978] [Hilton et al. 1975a] [Hilton et al. 1975c] [Hilton et al. 1975b] [Homans et al. 1978] [Hosier 1977] [Howard 1977] [Hubbard 1993] [Human Reaction to Aircraft 1989] [Humpert et al. 2015] [Hübner and Strümpfel 2020] [Ingram 1964] [Izquierdo et al. 2017] [Fowler et al] [Johansson 2023] [Jones 1946] [Ju et al. 2026] [Jäger et al. 2021] [Kayser et al. 2024] [Kelly 1993] [Kelly and Wilson 1995] [Kim et al. 2025b] [Knowd 1982] [Ko et al. 2026] [Komadina et al. 2002] [Kone et al. 2024b] [Koopmann 1976] [Kourbatski 2024] [Kozupa et al. 2023] [Krivosheikin and Perelygin 2015] [Kryter and Williams 1966] [Kukreja 2008] [Kurbjun 1959] [Large 1975] [Lee and Motsinger 1975] [Legriffon et al. 2023] [Hultgren et al. 2020] [Li 1981] [Li et al. 2020] [Lilley 2004] [Lilley 2006] [Lincke and Pieren 2024b] [Little and Russell 1976] [Mahak et al. 2017] [Maniet 2001] [Maria Thoma et al. 2024] [Matouk 2024] [Casanova et al. 2025] [McCracken 1979] [Khorrami et al] [Melton 1985] [Mengle et al. 2006] [Methods for Aircraft Noise 2011] [Metzger 1973] [Metzger and Worobel 1973] [Miguel 1974] [Miller and Eagan 1997] [Monitoring of Aircraft Noise 2011] [Morinaga et al. 2021] [Moses and Zeitlin 1975] [Muller 1971] [Munro and Ahuja 2003] [Nishinomiya et al. 1978] [Nnonyelu 2020] [Nnonyelu 2021] [Novak 1970] [Okada 1994] [Ollerhead 1982] [Olson et al. 2004] [Liem 2018] [Papamoschou and Debiasi 2003] [Park et al. 2026] [Paterson et al. 1973] [Peart 1991] [Pegg et al. 1974] [Peng et al. 2026] [Peterse 2024] [Pinker 2024] [Plucinsky 1973] [Posey 2008] [Pott-Pollenske 2021] [Qian 2026] [Queen and Cochrane 1982] [Raney 1975] [Rasband et al. 2023] [Raza and Stansbury 2025] [Riddle et al. 1981] [Riddle et al. 1987] [Rogers and Cook 1952] [Roxner and Postolsky 2024] [Rusciano and Viscardi 2008] [Sakaliyski et al. 2007] [Salikuddin 1990] [Sankar and Brentner 2008] [Schairer et al. 1971] [Schlinker 1979] [Schulze et al. 2024] [Schwab and Zellmann 2020] [Segall and Gardner 2026] [Shahady 1975] [Shapiro and Sherman Edwards 1967] [Shovlin et al. 1979] [Simson 2024] [Soderman 2006] [Soderman and Noble 1975] [Source Noise Suppression 1975] [Stephenson et al. 1990] [Stephenson et al. 2019] [Stoll et al. 2013] [Su et al. 2025] [Sunago et al. 2009] [Svane and Plovsing 2024] [Swearingen 2006] [Takaishi et al. 2023] [Takaishi et al. 2024] [Tam 2015] [Terashima et al. 2021] [The Inﬂuence of Operational 2011] [The Main Sources 2011] [Thorpe 1970] [Torija Martinez et al. 2023] [Tracy et al. 2002] [Trethewey 1988] [Tsutsumino et al. 2025] [Tweeddale 1941] [Typical Aircraft Noise Levels 1989] [Unruh 1980] [Wang and Antesberger 2024] [Wang and Crocker 1983] [Wang and Qin 2024] [Wang et al. 2022c] [Wang et al. 2023a] [Weston et al. 2024] [Wilkerson 1975] [Patterson et al] [Williams 1974] [Willis and Daniels 1981] [Willshire 1983] [Wilson 2025] [Wilson Committee Report 1963] [Xiang and Jiang 2015] [Xie et al. 2024] [Xu et al. 2025] [Yeong et al. 2009] [Yunus et al. 2023] [Zaporozhets and Jagniatinskis 2021] [Zellmann et al. 2018] [Zhang et al. 2023d] [Zhong et al. 2019] [Zorumski 1977] [Драмшини 2022, Development of Algorithms of the] [Тsekhmistro and Shapovalov 2023]

Performance, power required, endurance and range

Aircraft performance, power required, endurance, range, glide and sink rate, drag and fuel consumption.

Aeroelasticity, flutter and gust loads

Flutter, divergence, aileron reversal and buzz, gust loads and the flexible high aspect ratio wing. 138 of the 207 records date from 2015 or later.

207 records. [Abichandani and Rosenberg 1952] [Afonso et al. 2017] [Ahmadi and Farsadi 2024] [Ahmadi et al. 2024] [Alam and Hromcik 2019] [Alam et al. 2015] [Alexander 2025b] [Alighanbari 2002] [Anderson et al. 1973] [Araujo-Estrada and Windsor 2021] [Arnold 1942] [Awadalla Ali Haj Ahmed 2024] [Azzi et al. 2024] [Bachelder et al. 2023] [Balatti et al. 2021] [Balatti et al. 2023] [Banerjee 1984] [Banerjee 1988] [Bartels et al. 2017] [Bendiksen 1993] [Bergen and Arnold 1940] [Beyer et al. 2024] [Bi et al. 2017] [Bonomo and Chiarelli 2023] [Bowers et al. 2016] [Bras et al. 2022] [Bromfield and Dillman 2015] [Bromfield et al. 2023b] [Brown 1959] [Browne et al. 2025] [Burris and Bender 1969] [Cao et al. 2024] [Cavaliere and Fezans 2024] [Cecrdle 2011] [Changchuan et al. 2018] [Chen and Han 2017] [Chen et al. 2025c] [Cheung et al. 2020] [Chu and Widnall 1974] [Cole 1986] [Cole 1988] [Corwin et al. 1989] [Croom and Huffman 1957] [Birdsall 1970] [De Gaspari et al. 2024] [Della Vecchia et al. 2017] [Dickinson 1953] [Dilmi 2022] [Doggett and Soistmann 1992] [Douglas Aircraft Co Long Beach Ca 1962] [Duan and Zhang 2018] [Dussart et al. 2019b] [Eckhaus 1962] [Elyasi et al. 2020] [Farhat 1998] [Farhat 2000] [Farhat 2001] [Felt and Kehoe 1985] [Fournier et al. 2022] [Försching and Zingel 1988] [Gao et al. 2024a] [Gavrilovic et al. 2018] [Ghalandari et al. 2022] [Gimmestad 1980] [Goland 1952] [Gu et al. 2024] [Guimarães Neto 2025] [Guo et al. 2022] [Haftka 1977] [Hansen et al. 2022] [Hanson et al. 2014] [Hao et al. 2023] [Hicks et al. 2014] [Hillebrand et al. 2026] [Hoseini and Hodges 2019] [Hu et al. 2022] [Hu et al. 2026a] [Hui and Chen 2023] [Hunn 1953] [Ibren et al. 2020] [Iovnovich et al. 2018] [Jernell 1978] [Jones 1976] [Karpel 1990] [Khalil and Bauknecht 2024] [Khalil and Fezans 2020] [Khalil et al. 2022] [Kheiri and Riazat 2025] [Khuat et al. 2025] [Kilimtzidis and Kostopoulos 2023] [Kirsch et al. 2020] [Klein et al. 2017] [Klug et al. 2023] [Konar 2020] [Krawczyk et al. 2024] [Krzywoblocki 1943] [Kumar et al. 2025a] [Lagemann et al. 2024] [Le Clainche et al. 2019] [Lee et al. 2022b] [Levin and Katz 1984] [Leylek and Costello 2010] [Li and Qin 2020] [Li and Qin 2021] [Li and Qin 2022] [Li et al. 2024a] [Liu 2018] [Liu and Sun 2016] [Liu et al. 2017] [Liu et al. 2023] [Liu et al. 2026] [Lomax 1948] [Luderer and Thielecke 2025] [Malisani et al. 2021] [Mallik et al. 2015] [Mardanpour et al. 2018] [McCarthy et al. 1955] [McDonnell Aircraft Corp St Louis Mo 1950] [Mohamed et al. 2021] [Müller et al. 2026] [NACA Conference on Aircraft 1957] [Nagaraja et al. 1982] [Narimani et al. 2025] [Negahban et al. 2024] [Nejati et al. 2018] [Nguyen et al. 2017] [Nguyen and Xiong] [Oktay and ÖZen 2022] [Onkar et al. 2024] [Otsuka et al. 2021] [Otsuka et al. 2022] [Ouellette et al. 2026] [Portapas and Cooke 2020] [Pourtakdoust and Khodabakhsh 2026] [Pusch et al. 2019] [Pushtaev 1989] [Qi and Zhao 2020] [Qi et al. 2018] [Qiao et al. 2018] [Qiao et al. 2025] [Qu and Li 2022] [Quinn 1963] [Rankine and Leondes 1972] [Reed 1966] [Rehman 2022] [Rhoads 1952] [Rieck et al. 2026] [Bartels and Jacobson] [Rodden 1956] [Rodden 1989] [Rokhsaz and Kliment 2017] [Roos 1985] [Roskam and Dusto 1969] [Roskam et al. 1968] [Runyan et al. 1952] [Ryan Aeronautical Co San Diego Ca 1963] [Sabatini et al. 2026] [Sahyoun et al. 2026] [Saltari et al. 2017] [Shi and Wan 2015] [Silvestre and Luckner 2015] [Soneda et al. 2019] [Spada et al. 2017] [Steger and Bailey 1980] [Wright] [Sudha et al. 2018] [Suleman et al. 2016] [Swaim 1971] [Swaim and Connor 1968] [Swaim and Staab 1978] [Swaim and Yen 1979] [Szczyglowski et al. 2019] [Tang et al. 2016] [Tantaroudas and Karachalios 2026] [Teixeira and Cesnik 2020] [Thomson 1946] [Toffol 2024] [Tsatsas et al. 2022] [Ulvr et al. 2026] [Van Gaasbeek 1980] [Veley et al. 2008] [Versiani et al. 2019] [Wang 2019] [Wang and Chen 2024] [Wang et al. 2019a] [Wang et al. 2021] [Wang et al. 2022a] [Wang et al. 2022d] [Wang et al. 2026a] [Watson 1982] [Westin et al. 2023] [White 1971] [Willebeek-LeMair and Rhinehart 2023] [Wu et al. 2017] [Xie et al. 2017] [Xiong et al. 2026] [Yan et al. 2024a] [Yang and Li 2022] [Yang et al. 2016] [Yeager et al. 1997] [Yi et al. 2025] [You et al. 2020] [Zhang and Zhao 2023] [Zhang et al. 2026] [Zhao et al. 2023b] [Zheng et al. 2026] [Ziakos et al. 2025]

Flight test, system identification and parameter estimation

Flight test technique and management, system identification and parameter estimation from flight data, and flight test reports.

204 records. [Abramson 1975] [Abramson 1977] [Advisory Group for Aerospace Research and Development 1984] [Air Force Flight Test Center Edwards AFB CA 1970] [Air Force Flight Test Center Edwards AFB CA 1974a] [Air Force Flight Test Center Edwards AFB CA 1974b] [Air Force Flight Test Center Edwards AFB CA 1995] [Air Force Flight Test Center Edwards AFB CA 2002a] [Air Force Test Pilot School Edwards Afb Ca 1990e] [Air Force Test Pilot School Edwards Afb Ca 1990d] [Air Force Test Pilot School Edwards Afb Ca 1993] [Air Proving Ground Center Eglin AFB FL 1954] [Air Proving Ground Center Eglin AFB FL 1955b] [Air Proving Ground Center Eglin AFB FL 1955a] [Aircraft and Rotorcraft System 2016] [Alford 2004] [Alford and Knarr 1999] [Allen and White 1957] [American Institute of Aeronautics and Astronautics 1992] [Armstrong 1977] [Army Aviation School Fort Rucker Al 1961] [Arnold 1981] [Bachelder and Klyde 2011] [Baier 1970] [Barnette 1978] [Beale and Cook 1985] [Bender and O’Connor 1974] [Bennett et al. 1978] [Bleimeyer 1981] [Boeing Co Morton Pa Vertol Div 1961] [Brandon and Morelli 2016] [Brennan and McDaniel 1994] [Burt and Uselton 1976] [Bussolari et al. 1987] [Camponogara et al. 2019] [Carico 1998] [Che et al. 2021] [Choi 2025] [Grauer and Morelli 2025] [Liu 2024] [Manning et al. 1992] [Condon et al. 1970] [Cotton 1974] [Crawford and Hodgson 1961] [Cusimano and Johnson 1994] [Day and Guthrie 1958] [Day and Reisert 1959] [Deckert and Ferry 1959] [Deckert and Hodgson 1962] [Dias 2023] [Doko and Sasongko 2026] [Dong et al. 2024b] [Donizetti et al. 2023] [Dooley and Yeary 1979] [Du 2024] [Dunlap and Schalk 1956] [Dwyer 1994] [Evans and Schilling 1983] [Evans and Schilling 1984] [Faulcon and Monteith 1978] [Fechter and Mills 1988] [Feimin 2021] [Feng 2022] [Fenwick 1966] [Fenwick 1967] [Ferrell et al. 1974] [Fosdick 1970] [Burcham et al. 1992] [Freuler and Hoffmann 1977] [Gavurin 1965] [George et al. 2022] [Gera et al. 1981] [Gillard 1998] [Glenn and Midkiff 1951] [Gonczy 2015] [Grauer 2021] [Grauer et al. 2017] [Hamory and Murray 1993] [Hart 1992] [He and Ai 2018] [Holberg and Grabowsky 1981] [Hou and Song 2024] [Howell 1988] [Ignatyev et al. 2019] [Iliff and Maine 1984] [Irvine 1968] [Ishola et al. 2024] [Jategaonkar 2023] [Johnson and Anderson 1966] [Jones 1970] [Kayten and Koven 1945] [Kelley et al. 1990] [Kelly 1988] [Kim and Jeong 2026] [Kim et al. 2025d] [Kizer 1977] [Klein et al. 1982] [Klein et al. 1983] [Korsun and Moung Htang 2023] [Kulba et al. 2021] [Kumar and Ghosh 2018] [Kumar and Ghosh 2023b] [Kuppuswamy and Kiran 1981] [Li et al. 2025a] [Li et al. 2025b] [Lichota 2023] [Lichota et al. 2017] [Liu 1962] [Liu et al. 2015] [Lofthouse and Cummings 2017] [Lu et al. 2015] [Lustig et al. 1960] [Macmillan 1981] [Marston et al. 2015] [Martin 1978] [Matheny and Gatlin 1978] [Matsuki et al. 2018] [Mehra et al. 1972] [Mehra et al. 1974] [Michaels 1969] [Monstein et al. 2019] [Moralez et al. 2004] [Morelli and Cooper 2015] [Morris and Alexander 1978] [Narendra and Tripathi 1973] [Nash 1982] [Naval Air Test Center Patuxent River MD 1963] [Neves et al. 2020] [Nicolaides 1976] [North American Aviation INC LOS Angeles CA 1956] [North American Aviation INC LOS Angeles CA 1963] [Norton 1990] [Obermark 2004] [Ouda 2021] [Ovcharenko and Poplavsky 2021] [Palkin and Zenchenko 2025] [Park 2026a] [Park et al. 2018a] [Paulson and Shanks 1959] [Paulson and Shanks 1961a] [Pawlak 1994] [Peebles 2007] [Perkins et al. 1977] [Petersen 1981] [Hamory and Murray 1992] [Quanyan 2021] [Rediess and Melton 1994] [CHulin 2023] [Rhoads 1970] [Rice and Hazlwood 1994] [Roberts 1988a] [Rodden and Giesing 1970] [Sandstrom and White 1961] [Savory and Toy 1984] [Schade and Crane 1965] [Schofield 1984] [Schreadley 1977] [Schumacher 1952] [Seacord and Teitelbaum 1947] [Shi et al. 2023a] [Sibert 1947] [Sim and Curry 1978] [Simmons et al. 2023b] [Simmons et al. 2023c] [Simulation in Support 1988] [Srivastava 2016] [Stange 1959] [Strattan 1978] [Strier and Julian 1955] [Study on the Ground 2022] [Svendsen 1994] [Tai et al. 2023a] [Tai et al. 2024] [Tangler 1979] [Townsend and Phillips 1955] [Townsend and Phillips 1956] [Tracy 1981] [Traven and Whitley 1995] [Tsoubanos 1979] [Tusharika 2015] [Ulry et al. 1976] [Vagianos and Rooney 1964] [Van Pelt 1981] [Vaughn and Lindsay 1988] [Wang 2024] [Wang and Zhang 2020] [Wang et al. 2015b] [Wang et al. 2022e] [Wang et al. 2023b] [Ward 1988] [Watts 1976] [Wei and Renliang 2015] [Weiss et al. 1986] [Winn and Kishi 1972] [Xue and Haibin 2017] [Yancey 1964] [Yasue 2020] [Zajdel et al. 2022] [Zajdel et al. 2024a] [Zajdel et al. 2024b] [Zelenka et al. 1995] [Zhang 2024] [Zhang and Zhou 2024] [Zhou 2022]

Pilot training, simulation, human factors and safety

Pilot training and selection, simulators and their fidelity, startle and surprise, workload, human factors and aviation safety. 106 of the 189 records date from 2015 or later.

189 records. [Abramov et al. 2019] [Adolph 1981] [Aguiar and Cuevas 2017] [Aguiar et al. 2017] [Air Force Flight Test Center Edwards AFB CA 2002b] [Air Force Test Pilot School Edwards Afb Ca 1962c] [Aircraft Safety Office 1971] [Moscow and Aleksandrov 2025] [Allen et al. 2000] [Aláez et al. 2022] [Army Aviation Center and Fort Rucker AL 1992] [Atmaca et al. 2025] [Badzli 2023] [Bagley et al. 2026] [Baisden 1980] [Beard et al. 2013] [Borst 1978] [Bortolussi 1997] [Boyd 2015a] [Boyd 2015b] [Boyd and Stolzer 2016] [Bray and Larsen 1965] [Brian Trubshaw 2006] [Bronder et al. 2012] [Bynum 1978] [Cain 1979] [Carico] [Carico et al] [Carico et al. 2001b] [Caro 2017] [Carroll et al. 2021] [Causse et al. 2026] [Chappelle et al. 2014] [Chen et al. 2025a] [Chen et al. 2025b] [Chen et al. 2025d] [Chen et al. 2026d] [Clewley and Nixon 2019] [Clothier et al. 2015] [Clousing 1965] [Cornell Aeronautical Lab INC Buffalo NY 1947] [Cotting 2016] [Craig et al. 1999] [Cross and Ryley 2024] [Cunningham 1962] [The U.S. Air Force 2005] [Diarra et al. 2023] [Dohme 1981] [Donateo and Totaro 2019] [Dong et al. 2024a] [Dreyfus and Dreyfus 1979] [Du et al. 2024] [Duchevet et al. 2025] [Dusterberry 1964] [Eppley 1963] [Eshmuradov and Bekbaev 2023] [Gerdes 1977] [Machine Learning-Based Spatial Disorientation 2024] [Morelli] [Gardini et al. 2022] [Geister et al. 2017] [General Electric Co Schenectady Ny 1952] [Gilbert et al. 1976] [Gleason et al. 1996] [Grantham et al. 1984] [Grantham et al. 1985] [Grether 1973] [Griffin and McBride 1986] [Grindley et al. 2025] [Gu 2025] [Guldal and Andersson 2020] [Guthridge 2025] [Harnyoot 2018] [Hart 1956] [Hart 1984] [Hashii and Thompson 2018] [Henderson 2022] [Hess 1977] [Hjellvik and Mallam 2024] [Houston et al. 1954] [Hunter and Burke 1992] [Intano and Howse 1991] [Irsyad Lukman and Agoes Moelyadi 2018] [Jiao et al. 2022] [Johnson 1975] [Jolley and Caro 1970] [Litt et al. 2022] [Justiz and Patel 1988] [Kellogg 1946] [Kibbee 1978] [Kim 2020] [Kim and Kim 2020] [Kyrpenko 2015] [la Cour-Harbo 2018] [Landman et al. 2017] [Landman et al. 2020] [Lang 1981] [Lee et al. 2021] [Leonidov 2025] [Li et al. 2023d] [Lilla et al. 2025] [Litt et al. 2012] [Liu et al. 2018] [Haworth et al] [Löhr and Haines 2024] [MacDonald and Shepherd 2008] [Mamich et al. 2025] [Ogburn et al. 1991] [McAree et al. 2018] [Metodiev 2024] [Middleton et al. 1975] [Miller and Khinoo 1994] [Minor 2008] [Mostarac et al. 2022] [Murray et al. 1992] [Myers et al. 2018] [Na and Cho 2022] [Navaratna et al. 2019] [Neff 2019] [Northrop Aircraft INC Hawthorne CA 1952] [Oh and Yoon 2022] [Harendra et al. 1973] [Paullin et al. 2011] [Pauls and Gollnick 2025] [Pavlusíková and Chodelka 2023] [Petitt 2017] [Pleban and Beal 2002] [Powell-Dunford et al. 2016] [Primatesta et al. 2019] [Pugh 1972] [Quinn and Breidenbach 1978] [Ratvasky et al. 2003] [Rawson 1963] [Reising et al. 1996] [Research and Analysis 2022] [Rey et al. 2021] [Reynolds et al. 2018] [Ringland and Craig 1977] [Roberts and Brown 1988] [Roberts and Shawler 1994] [Rusakov and Krupetskyh 2012] [Saastamoinen and Maunula 2021] [Saravo 1976] [Schollenberger et al. 2025] [Schwartz and Wray 1969] [Serra and Branco 2026] [Seville Research Corp Pensacola FL 1979] [Shafer 1991] [Shafer 1992] [Shannon and Wang 1973] [Sharma 2016] [Simmons 2023] [Sims and Kimberlin 1995] [Siqueira et al. 2025] [Socha et al. 2026] [Somerville et al. 2025] [Somerville et al. 2026a] [Somerville et al. 2026b] [Spanò Cuomo and Guglieri 2021] [Sun 2026] [Surkova et al. 2025] [The Development of Aviation 1948] [Trollip 1977] [Truong et al. 2024] [Vicory 1968] [Vidović et al. 2022] [Vitsas 2016] [Vlaskamp et al. 2025a] [Vlaskamp et al. 2025b] [Vlaskamp et al. 2026b] [Vlaskamp et al. 2026a] [Walker 2015] [Walker 2024] [Walker et al. 2016] [Warner 1993] [Washington et al. 2017] [Watson et al. 2020] [Wei et al. 2022a] [Wesolek 2007] [Yazgan and Kucuk Yilmaz 2018] [You 2020] [Yusuf et al. 2022] [Zaal et al. 2015] [Zeller and Gary 2001] [Zhang et al. 2025b] [Zikmund et al. 2019] [Şenol 2020] [Дмитренко 2024] [Задкова 2015, Pilots Errors Accounting and]

Lateral control, ailerons and adverse yaw

Ailerons, spoilers and rudders, the rolling and yawing moments they produce, and adverse yaw. 75 of the 181 records date from before 1970.

This is the X-26A’s keystone literature, and it is old. The yawing moment of a deflected aileron was measured and tabulated in the decades before the aircraft flew, which is why the subject is documented under the period’s vocabulary of ailerons, yawing moment and lateral control.

181 records. [Adams 1951] [Altman 1952] [Arena et al. 1993] [Ashkenas 1946] [Baker 1941] [Becker and Korycinski 1944] [Bennett and Johnson 1947] [Bischoff et al. 1974] [Braslow 1944] [Braslow and Visconti 1949] [Cobleigh et al. 1994] [Bretoi 1952] [Brincklow and Hunsaker 2021] [Brincklow et al. 2021] [Brincklow et al. 2024] [Bruington et al. 2001] [Campbell and Goodman 1949] [Cancro 1953] [Shubham Prakash Rawool 2017] [Chen et al. 2026c] [Childress 1958] [Christophersen and Spahr 1944] [Claudia Alice 2010] [Cliff and Lutze 1972] [Cobleigh 1994] [Crandall 1943] [Crane and Holtzclaw 1944] [David and Seifert 2012] [Davis 1957] [De Gaspari and Mantegazza 2024] [Dennis and Scherrer 1951] [Deters and Russell 1947a] [Deters and Russell 1947b, Investigation of the Aileron and] [Di Donato et al. 2017] [Duerksen 1997] [Eggleston and Diederich 1957] [El-Ramly et al. 1976] [Ellerbroek et al. 2007] [Ellis 1972] [Esparza 1975] [Failure of an Aileron 2005] [Fehlner 1942] [Fischel and Schneiter 1947] [Fournier and Silvers 1958] [Graham 1945] [Gregorek 1984] [Gregorek 1995] [Guo et al. 2020] [Hall and Boothe 1972] [Hall and Mason 2012] [Hammond and Henderson 1961] [Haque et al. 2016] [Harman 1944] [Helicopter Yaw Control 1990] [Higgins and Jacobs 1928] [Hoholis et al. 2016] [Hopkins and Lovette 1977] [Hu et al. 2025] [Huang and Wu 2006] [Hunsaker et al. 2019] [Hunsaker et al. 2020a] [Hunsaker et al. 2020b] [Hunsaker et al. 2021] [Huzita 1971] [Ivey 1945] [Jacobs 1983] [Jacobs and Bartlett 1981] [James and Vaughn 1976] [Jayalakshmi et al. 2021] [Jennings 1931] [Jeong et al. 2015] [Jiang 1999] [Jiang et al. 2000] [Johnson and Hagerman 1950] [Johnson and Sternfield 1948] [Kelley and Enevoldson 1981] [Kelly and Brown 1980] [Kemp 1943] [Kigotho et al. 2022] [Kohlman 1977] [Kou et al. 2021] [Kowalska and Goetzendorf-Grabowski 2022] [Krishnan et al. 2020] [Levy 1992] [Li and Yang 2017a] [Li and Yang 2017b] [Li et al. 2022b] [Lovell and Stassi 1950] [Luoma 1944] [Ma et al. 2023] [MACKlNNON and Madden 1972a] [Mao and Zhao 1990] [Andino et al] [Martina 1953] [Martina 1954] [Masud et al. 2016] [McKee 1943] [McLaughlin and Shaw] [Molchanov 1981] [Moore and Moore 2012a] [Moore and Moore 2012b] [Moul and Brown 1979] [Munk 1925] [Murray and Warren 1944] [Myala et al. 2020] [National Advisory Committee 1937] [National Advisory Committee 1932] [Nazarenko and Nevezhina 1972] [O’Donnell and Mohseni 2019] [Ogawara et al. 2024] [Pamadi and Pai 1980] [Paulson 1976] [Pearson 1937] [Phillips 1942] [Platt and Shortal 1937] [Purser 1941] [Qian et al. 2022] [Qin et al. 2014] [Qiu and Ang 2019] [Qu et al. 2017] [MacLeod 1952] [R. 1935] [Radetskaya 2022] [Rao 1992] [Rao et al. 1987] [Report No. 423 Wind-Tunnel 1932, Report No. 423, Wind-tunnel] [Report No. 439 Wind-Tunnel 1932, Report No. 439, Wind-Tunnel] [Report No. 444 Wind-Tunnel 1932, Report No. 444, Wind-Tunnel] [Report No. 510 Wind-Tunnel 1935, Report no. 510, wind-tunnel] [Platt 1935] [Rosenberg 1944] [Sachs and Moelyadi 2006] [Sandu et al. 2025] [Schneiter and Watson 1948] [Sekaran 1983] [Shankar and Yathisha 2023] [Shearwood et al. 2020] [Shmilovich et al. 2023] [Shmilovich et al. 2026] [Shortal 1934] [Sinkovec et al. 2015] [Sohail et al. 2011] [Soinne 1999] [Soule and Wetmore 1933] [Spearman and Webster 1951] [Stewart 1939] [Stewart 2008] [Tavella et al. 1987] [Tay et al. 2025] [The Pearson Rotary Aileron 1930] [The Simplification of Lateral 1936] [Toll 1943] [Underwood 1942a, Aerodynamic Characteristics for] [Vechtel and Buch 2022] [Venkataraman and Seiler 2019] [Wang et al. 2013] [Wei et al. 2017] [Weick and Harris 1933] [Weick and Harris 1934] [Weick and Jones 1937] [Weick and Jones 1976] [Weick and Noyes 1933a] [Weick and Noyes 1933b] [Weick and Shortal 1933] [Weick and Shortal 1935] [Weick and Wenzinger 1935] [Weisshaar 1977] [Weisshaar 1990] [Wenzinger and Bamber 1938] [Wenzinger and Rogallo 1941] [Whitaker 1975] [Whiting 1996] [Wiley 1954] [Wiley and Taylor 1954] [Wilson 1918] [Wu et al. 2020c] [Xiong et al. 2025] [Yan et al. 2024b] [Yeo et al. 2015] [Zhang et al. 2013] [Zuhri 2025]

Sailplanes, gliders and soaring

Sailplanes, gliders, motor gliders and soaring flight, including the design, performance and flight test of sailplanes and the dynamic soaring of unmanned aircraft.

The sailplane is a research instrument in its own right. The cluster includes sailplanes used for boundary layer, turbulence and post-stall research, and a record on teaching flight testing through soaring.

178 records. [A Sailplane Wing Constructed 1974] [Achleitner et al. 2019] [Aero Structural Optimization 2018] [Allen 2006] [Allen 2007a] [Allen 2007b] [Amalia et al. 2018] [Amalia et al. 2019] [An Evaluation of Sailplane 1974] [Anderle et al. 2003] [Axten and Maughmer 2020] [Axten et al. 2024] [Barnes 2015] [Bennett 1978] [Bennett et al. 1974] [Bonnin] [Bonnin et al. 2013] [Boyer 1908] [Bozack 1984] [Bramesfeld and Maughmer 2002] [Brodsky and Luby 2013] [Brown 1954] [Bucur and Lupuleasa 2026] [Budd and Monheim 2015] [Cao 2023] [Chen] [Cheng and Langelaan 2014] [Chick et al. 2023] [Collazo Garcia et al. 2019] [Colling 1995] [Computational Simulation of F3F 2025] [Czarnocki et al. 2019] [Guido 1991] [d and de Socio 1999] [d and Menichetti 2000] [Dandwani et al. 2025] [de Matteis and Tamilia 1993] [Dees 2010] [Dees 2013] [Deittert et al. 2009] [Demircali and Uvet 2017] [Demircali and Uvet 2018] [Deprez 1908] [Dubnický et al. 2023] [Dudek et al. 2020] [Dutta 2026] [Edwards 2015] [Erb et al. 2009] [Genalo] [Genalo and Pierson 1978] [Gliding and Soaring Flight 1938] [Grossman et al. 1986] [Göksel] [Heinrich et al. 1964] [Horstmann and Quast 1980] [Huang et al. 2006] [Instruments for Soaring Flight 1999] [Irving 1999] [Janzen and Precourt 1989] [Johnson 1949] [Kakade et al. 2022] [Kehoe and Ellison 1985] [Kensche 2003] [Kentfield 2012] [Keskin et al. 2021] [Klemin and Walling 1943] [Kochersberger et al. 2003] [Koessler 2018] [Kohne et al. 2024] [Krebs and Bramesfeld 2016] [Krebs and Bramesfeld 2017] [Kroo 2000] [Kubrynski 2012] [Kuettner 1952] [Kulhánek 2019] [Kumar et al. 2026] [Kuźniar and Orkisz 2019] [Ladeira et al. 2024] [Lamp and Luckner 2013] [Larrabee 1974] [Lauk and Unt 2015] [Lauk et al. 2017] [le Roux et al. 2025] [Lendraitis 2019] [Lin 2007] [Lindstedt et al. 2019] [Lippisch 1930] [Lippisch 1935] [Lorenz 1985] [Lundberg 1937] [Lundberg 1938] [Lupp and Cesnik 2015] [MacCready 1962] [Madelung 1923] [Marsden 1974] [Maughmer] [Maughmer 2003] [Maughmer et al. 2024] [McMasters 1979] [McMasters and Palmer 1975] [Metzger 1974] [Miller 1985] [Mulyanto and Zulkarnain 2020] [Mulyanto and Zulkarnain 2021] [Muser 1979] [Nash-Webber 1973] [Neto and Signor 2023] [Oliveira et al. 2021] [Orkisz et al. 2019] [Pfeiffer 2017] [Pierson 1977] [Pierson and Chen 1979a, Minimum Altitude-Loss Soaring in] [Pierson and Chen 1979b] [Pierson and De Jong 1978] [Pilcher 2021] [Poznanski et al. 2025] [Puttur and Layng 2025] [Raffel et al. 2019] [Ramšak 2012] [Range et al. 2013] [Raspet 1952] [Raspet 1955] [Reeder 1959] [Report No. 434. Lift 1932, Report No. 434. Lift and drag] [Reussner 1950] [Reussner 1953] [Hoey 1992] [Romadhon et al. 2024] [Rosales et al. 2021] [Sachs and da Costa 2003] [Sachs and Grüter 2017] [Sachs et al. 2013] [Sakamoto and Cota 1965] [Sakamoto et al. 2007] [Sampaio et al. 2014] [Sandlin and Saiki 1993] [Satuluri and Seeni 2022] [Schreder 1975] [Scientific and Technical Aspects 1952] [Shenstone 1938] [Shenstone 1946] [Shenstone 1953] [Shrey. J. Mistry et al and TJPRC 2018] [Silvestre 2013] [Sim 1990] [Sinha and Ravande 2006] [Slater 1955] [Sliwa and Sliwa 1979] [Somers 1977] [Somers 1981] [Somers and Foster 1979] [Stewart 2016] [Suzuki and Kawamura 1995] [Suzuki and Kawamura 1996] [Swaminathan and Mohan 2018] [Taylor 2011] [Tetlow 1983] [The Drag 1999] [The Sailplane as 1948] [The Sailplane 1999] [Thomas 2003] [Turner 1942] [Turriziani 1979] [Vilchis Medina et al. 2018] [Medina et al. 2019] [Voß and Ohme 2018] [Ward and Bennett 1974] [Wei et al. 2022b] [Welch 1995] [Wiggi 1949] [Wilk 2024] [Wilkinson 1954] [Wolek et al. 2016] [Yamin and Giyats 2022] [Yates 1949] [Yu 2026] [Zhang et al. 2011] [Zhao 2025]

Outdoor sound propagation and atmospheric absorption

Spherical spreading, atmospheric absorption, refraction, ground effect and turbulent scattering, with the duct propagation that shares their equations. 70 of the 165 records date from 2015 or later.

165 records. [Abrahamson 1975] [Aircraft Noise Propagation 2011] [Albert 1990] [Albert 2004] [Almgren 1987] [André 1977] [Attenborough 1985] [Attenborough 2022] [Aurégan 2018] [Bass 1976] [Bass et al. 1972] [Bass et al. 1990] [Bauer 1977] [Becher et al. 1981] [Bishop and Franken 1967] [Bishop and Franken 1968] [Blumenfeld and Weiss 1975] [Brown 1950] [Burrin 1970] [Canard-Caruana et al. 1990] [Carnes et al. 1993] [Carr et al. 2024] [Castro Mota et al. 2025] [Chessell 1978] [Chobeau et al. 2017] [Cole and Dobbins 1970] [Cole and Dobbins 1971] [Crighton 1979] [Davidson 1975] [Dean 1979] [DeLoach 1975] [Diamond 1963] [Diamond and Lee 1965] [Dickinson 1976] [Dickinson 1979] [Doak and Vaidya 1970] [Doebler et al. 2023] [Domen 1998] [Downing et al. 1996] [Dragna and Blanc-Benon 2017a] [Dragna and Blanc-Benon 2017b] [Ecotière 2023] [Eser 2023] [Evans 1975] [Evans et al. 1972a] [Evans et al. 1972b] [Fidell et al. 1989b] [Finn and Rogers 2015] [Finn and Rogers 2016a] [Finn and Rogers 2016b] [Foss 1979] [Goestchel et al. 2022] [Groves 1955] [Groves 1956a] [Groves 1956b] [Gu et al. 2026] [Hall et al. 2016] [Hart et al. 2016] [Hart et al. 2021] [Henyey 2009] [Hilton and Kasper 1974] [Hohenwarter et al. 2022] [Hussain and Dutilleux 2020] [Jeff Berton] [Jeffery et al. 1977] [Jing and Ye 2021] [Joel B Lonzaga, An exact solution of an augmented] [Joel B. Lonzaga, Nonlinear Acoustic Propagation in] [Kamrath 2022] [Kamrath et al. 2016] [Kapoor et al. 2021] [Ke and Zheng 2016] [Keshavarz and Ohadi 2017] [Keyel et al. 2017] [Kim and Lee 2024] [Kingan et al. 2023] [Kirby 2021a] [Kirby 2021b] [Kirby 2022] [Knudsen 1946] [Kone et al. 2023] [Kone et al. 2024a] [Kraichnan 1954] [Kraxberger et al. 2024] [Kriebel 1972] [Laly et al. 2023] [Lee and Sutherland 1976] [Letcher 1995] [Loubeau 2021] [Lyon and Pande 1971] [Marsh 1981] [Mechel 1962] [Mechel et al. 1963] [Mellish et al. 2020] [Meredith et al. 1981] [Mo et al. 2016] [Mo et al. 2017] [Mobley et al. 2016] [Morfey and Howell 1980] [Morfey and Howell 1981] [Morfey and Tester 1977] [Mungiole and Wilson 2003] [Nayfeh 1980] [Norris and Ostashev 2022] [Nyborg and Mintzer 1955] [Ohm et al. 2020] [Oncley 1970] [Ostashev and Goedecke 2005] [Ostashev and Wilson 2022] [Ostrikov et al. 2020] [Pao and Evans 1971] [Parry et al. 2020a] [Parry et al. 2020b] [Pasareanu et al. 2018] [Pena and Diamond 1965] [Peplow and Liu 2025] [Plotkin and Shepherd 2006] [Polly 1969] [Pridmore-Brown 1962] [Putnam 1975] [Rasmussen 1986] [Rasmussen 1990] [Richards and Attenborough 1986] [Ruijgrok 1983] [Ryan et al. 2022] [Rydin et al. 2018] [Sabine and Burkhard 1959] [Salomons et al. 2016] [Schwartz 1976] [Shankar 1972] [Shields and Bass 1977] [Shivashankara and Stubbs 1987] [Soom and Gu 1981] [Southerland et al. 1986] [Stenzel 1947] [Sutherland and Wesler 1990] [Swearingen and White 2020] [Takeya and Okumoto 1959] [Tester 1973b] [Tester 1973a] [Tipton and Sparrow 2019] [Tombolato et al. 2024] [Trikootam and Hornikx 2019] [Troian et al. 2017] [Vecchiotti et al. 2024] [Veldkamp 1951] [Wang and Li 2019] [Wang et al. 2024c] [West 1994] [West et al. 2015] [White 2025] [White and Swearingen 2004] [Willshire 1990] [Willshire and Hilton 1979] [Wilson 2024] [Wilson et al. 2016] [Wilson et al. 2022] [Wolf and Raspet 1986] [Woolworth 2022] [Woolworth 2023] [Yamashita and Matsui 1978] [Yokota et al. 2023] [Yokota et al. 2025] [Zheng et al. 2019] [Zorumski and Willshire 1989]

Flying and handling qualities

Flying and handling qualities, their criteria and specifications, pilot rating and the course texts of the test pilot schools.

Lateral-directional stability, roll damping and coupling

Static and dynamic lateral-directional stability, roll damping, sideslip, Dutch roll and the coupling of roll and yaw. 44 of the 158 records date from before 1970.

158 records. [Abdul Rashid et al. 2025] [Adams 1976] [Air Force Test Pilot School Edwards Afb Ca 1989] [Air Force Test Pilot School Edwards Afb Ca 1990c] [Aircraft Lateral-Directional Handling Qualities 2011] [Akishita et al. 1986] [Albostan and Gökaşan 2018] [Alston 1936] [Ananthkrishnan and Sinha 2023] [Arabian and Schmeer 1955] [Ashkenas 1965b] [Ashkenas 1965a] [Bailey et al. 1988] [Baker 1948] [Banerjee et al. 2017] [Baroff 1980] [Bian et al. 2019] [Bird and Jaquet 1951] [Bird et al. 1952] [Bischoff and Palmer 1983] [Boyden 1971] [Bradley 1975] [Brown 1981] [Brown and Adams 1948] [Brown and Heinke 1956] [Burken et al. 1996] [Burt 1975] [Butler 1976a] [Butler and Langham 1978] [Calloway 1983] [Chalk 1983] [Chambers 1966] [Chevalier and Burke 1972] [Ciliberti and Nicolosi 2025] [Coe and Newsom 1974] [Coe et al. 1975] [Coletti 1954] [Crane and Reeder 1945] [Dahiya 2016] [Dahiya 2017] [Davari and Laitone 1977] [DeSanti 1988] [Eastman 1986] [Er-El et al. 1989] [Esteban et al. 2015] [Fajar and Arifianto 2018] [Fetterman and Penland 1960] [Fink et al. 1970] [Franklin 1971] [Frierson et al. 1978] [Fu et al. 2020] [Ganiev 1978] [Garcia-Baquero et al. 2018] [Gates and Sternfield 1950] [Goglia and Arunkumar 1983] [Grunwald 1961] [Gu 1986] [Gundry 1977] [Guruswamy 2021a] [Guruswamy 2021b] [Hacker 1977] [Hamel 1970] [Hancock 1972] [Hawks 1982] [Healy et al. 2022] [Hewes 1959] [Higgins et al. 2020] [Hwang and Pi 1978] [Hwang and Pi 1979] [Iliff and Wang 1996] [Iliff and Wang 1997] [Iliff and Wang 1999] [Jenke 1976] [Jeong et al. 2024] [Johnston et al. 1965a] [Jones 1950b] [Katz and Levin 1986] [Khanna et al. 2022] [Kuhn 1981] [Kumar and Ghosh 2023a] [Lichtenstein 1952] [Lichtenstein and Williams 1961] [Linehan and Mohseni 2016] [Loomis and Porter 1965] [Lungu and Lungu 2015] [Lungu and Lungu 2016] [Lyu et al. 2022] [Ma et al. 2019] [MACKlNNON and Madden 1972b] [Malvestuto et al. 1950] [Martin and Gerber 1953] [McNeill and Innis 1965] [Meissner 1973] [Miles 1952] [Miller and Franklin 1968] [Mitchell and Hoh 1984] [Mohamed and Joy 2021] [Mohammadi Farhadi et al. 2018] [Motyka and Hall 1973] [Murrieta-Mendoza et al. 2016] [Navaratna et al. 2022] [Ni et al. 2025] [Ogren et al. 1974] [Ohta et al. 1979] [Ohta et al. 1982] [Pavithra 2019] [Pan and Huang 2019] [Peron and Carpenter 1992] [Petersen et al. 1962] [Polhamus and King 1949] [Posingies 1968] [Price 1943] [Putman 1969] [Rajeswari and Padma Suresh 2015] [Raney and Batterson 1989] [Rossow 1986] [Sanghi et al. 2024] [Schade et al. 1952] [Scherrer and Dennis 1951] [Schieni et al. 2024] [Schy and Hannah 1977] [Schütte and Hummel 2023] [Seckel and Graziani 1956] [Sen et al. 1987] [Shen et al. 2021] [Shrivastava and Stengel 1989] [Siddiqui et al. 2023] [Smith 1982] [Snell 1993] [Snell et al. 1991] [Sommer and Tapscott 1966] [Sponder 1950] [Stengel 1975] [Stengel 1980] [Sternfield 1954] [Stone 1945] [Suarez et al. 1993] [Suit and Batterson 1986] [Swarnkar and Kothari 2016] [Szalai 1967] [Sánchez et al. 2024] [Tai et al. 2023b] [Tai et al. 2025] [Teper and Stapleford 1966] [Thomson 1947] [Tobak and Schiff 1975] [van Gool 1982] [van Rooyen and Eshelby 1981] [Velger and Shinar 1983] [Vidan 2016] [Vomaske et al. 1961] [Walchner 1969] [Walchner et al. 1969] [Wang et al. 2022b] [Wells et al. 1982] [Wu et al. 2018] [Yin et al. 2020] [Zhai et al. 2024]

Community noise, annoyance and psychoacoustics

Annoyance, community response, health effects and the psychoacoustic metrics that predict them, for aircraft and for the urban air mobility vehicles now proposed. 96 of the 146 records date from 2015 or later.

146 records. [Aalmoes and Sieben 2021] [Abwanzo 2016] [Aircraft Noise and Certification 2019] [Aircraft Noise Monitoring 1979] [Akdeniz et al. 2020] [Akiyama et al. 2023] [Alexandre and Barde 1974] [Baudin et al. 2021] [Christian] [Ang et al. 2024] [Bauer 2021] [Bauermeister and Donner 1980] [Bolt Beranek and Newman INC LOS Angeles CA 1965] [Boucher et al. 2023] [Boullet et al. 2023] [Calculation of Aircraft Noise 1989] [Chabot and Bird 2015] [Christian 2021] [Clemente Carrari et al. 2025] [Curtis 1977] [Dani] [Di 2017] [Felcyn and Ptak 2022] [Fidell 2018] [Fidell et al. 1998] [Flindell et al. 2021] [Galloway and Bennett 1981] [Gasaway 1970] [Georgiou et al. 2026] [Gille and Marquis-Favre 2019] [Gille et al. 2017] [Gillfillan 1961] [Gillfillian 1962] [Gjestland 2018] [Green et al. 2023] [Guerrero et al. 2026] [He et al. 2026b] [Hede 2017] [Higbie 1995] [Hiramatsu 2023] [Holger 1980] [Howie and Brugger 2000] [Huang et al. 2023a] [Iemma 2016] [Jovanovic and Novak 2022a] [Jovanovic and Novak 2022b] [Jovanovic et al. 2022] [Jovanovic et al. 2023] [Kafali and Güçlü 2023] [Keilman 2019] [Kim] [Kim et al. 2022a] [Ko 1975a] [Ko 1975b] [Ko 1979] [Kodji et al. 2023] [Kodji et al. 2024] [Krishnamurthy and Rizzi 2022] [Kryter 1966] [Kryter 1967] [Kryter 1982] [Kryter and Pearsons 1962] [Kuhlmann et al. 2024] [Kull and Finegold 2024] [Kyi and Feng 2026] [König et al. 2024] [Lang 2024] [Lechner et al. 2019] [Lechner et al. 2021] [Lee et al. 2026] [Li et al. 2021] [Lincke and Pieren 2024a] [Lincke et al. 2025] [Lotinga et al. 2025a] [Lotinga et al. 2025c] [Lotinga et al. 2025b] [Ludlow 2024] [Lv et al. 2023] [Mackie and Lawrence 2019] [Marquis-Favre et al. 2021] [Marquis-Favre et al. 2023] [McCurdy 1984] [McNeill and Vomaske 1959] [McPIKE 1972] [McPike 1976] [Melton and Jacobson 1983] [Min et al. 2015] [Monzambe et al. 2024] [Nguyen and Yano 2024] [Nguyen et al. 2018] [Odell 1977] [Ollerhead 1973] [Page et al. 2021] [Page et al. 2026] [Papamoschou and Phong 2018] [Phun et al. 2015] [Raw and Griffiths 1985] [Reddingius 1974] [Reddingius 1977] [Reeves et al. 2023] [Rehm and Jansen 1978] [Rizzi and Rafaelof 2021] [Rizzi and Scata 2022] [Rizzi et al. 2016] [Rizzi et al. 2024] [Roberts 1988b] [Roncen 2025] [Sahai et al. 2017] [Sawyer 1967] [Scanlan 1948] [Schaffer et al. 2023] [Schomer et al. 1991] [Schreckenberg et al. 2023] [Schäffer et al. 2020] [Speakman et al. 1978] [Sperry 1979] [Stewart et al. 2012] [Tarnopolsky 1978] [Taylor 1984] [Terzakis et al. 2025] [Thalheimer 2021] [Thirtyacre et al. 2021] [Thomas and Hansman 2019] [Thomas and Hansman 2020] [Thomas and Hansman 2021] [Thomas and Jones 1982] [Thottathil Varghese et al. 2022] [Tokashiki 2023] [Tracy et al. 2024] [Vaughn et al. 2023] [Vulkan and Hyde 1981] [Bauer 2025] [Wang et al. 2015a] [Webster 1971] [Welch et al. 2026] [Weslet and Sutherland 1987] [Woods 1972] [Wothge et al. 2017] [Wu and Redonnet 2021] [Yamada 2023] [Yeow 1984] [Yoon et al. 2019] [Zaporozhets et al. 2022] [Zhang et al. 2023b] [Zhang et al. 2025a] [ZoriĆ 2024]

Induced drag, span loading and the high aspect ratio wing

Induced drag, span loading, lifting-line and lifting-surface theory, winglets and the high aspect ratio wing.

146 records. [Adamson and Boatright 1950] [Ajaj 2021] [Antonakis and Biannic 2024] [Army Aviation Board Fort Rucker Al 1957] [Ashill 1970] [Barrett-Gonzalez and Wolf 2021] [Bauer et al. 2016] [Baykal et al. 2024] [Bera 1976] [Bera† 1980] [Bilanin and Donaldson 1975] [Bloom and Jen 1974] [Bobbitt 1957] [Bobbitt 1959] [Bowers 1979] [Bowers 2018] [Nan et al. 2024] [Thinesh and Harmin 2018] [Chakraborty et al. 2015] [Chau and Zingg 2022a] [Chau and Zingg 2022b] [Chau and Zingg 2023] [Chau et al. 2026] [Cheng 1978] [Cheng and Meng 1980] [Cook 1979] [Curtiss 1965] [Dalton and Wang 1990] [Deyoung 1950] [Deyoung 1979] [Deyoung and Harper 1948] [Dragos 1985] [Dragoş 1990] [Dym and Williams 2015] [Feero et al. 2016] [Flechner and Jacobs 1978] [Fu et al. 2021] [Gaifullin 2023] [Gilbrook et al. 2025] [Golubinskii and Golubkin 1983] [Golubkin 1980a] [Golubkin 1980b] [Goodman 1976] [Graham 1971] [Griffin et al. 1983] [Hall et al. 1994] [Hanin and Barsony-Nagy 1983] [Hanks 1956] [Harry and Trobaugh 1966] [He et al. 2020] [Higuchi et al. 1987] [Hoerner 1952] [Hopkins 1977] [Hosseini et al. 2020] [James 1975] [Jang and Ahn 2022] [Johnson 1972b] [Jones 1950a, The spanwise distribution of lift] [Kacik and Goetzendorf-Grabowski 2025] [Katz 1989] [Keener 1985] [Kennelly et al. 1990] [Kholyavko 1971] [Kiang 1971] [Kida 1982] [Kida and Miyai 1978] [Kretov and Tiniakov 2022] [Kuhlman 1979] [Kuhlman and Liaw 1987] [Lazos and Visser 2006] [Lee et al. 2017b] [Lerbs 1955] [Levinsky et al. 1968] [Li et al. 2022a] [Li et al. 2023c] [Loth and Boyle 1969] [Lundry 1977] [Ma 1989] [Ma et al. 2022a] [Ma et al. 2026] [Malmuth 1966] [Mamada and Ando 1974] [Mansour 1985] [Marchman and Abtahi 1985] [Martinez 1989] [McCormick 1959] [McCutchen 1989] [Menon et al. 2022] [Miles 1953] [Milla and Blick 1966] [Mitcheltree et al. 1986] [Mokry and Rainbird 1975] [Morita 1970] [Morita 1971a] [Morita 1971b] [Moriya 1972] [Morton 1956] [Mr. S. Aravindan et al. 2017] [Narayan 1975] [Nelson 1964] [Nonweiler 1960] [Pao and Lan 1978] [Pavel et al. 2018] [Pavlenko and Reslan 2022] [Pelykh and Andryushchenko 2024] [Perry 1978] [Pfeifle et al. 2022] [Portnoy 1976] [Portnoy 1977] [Pyo 1995] [Quinn et al. 2025] [Stallings 1986] [Rand et al. 2004] [Reynolds 1963] [Rice and Oetting 1976] [Ruffini et al. 2020] [Kandasamy et al. 2018] [Sanz 1986] [Schauerhamer and Robinson 2017] [Schulderfrei et al. 1951] [Sears 1948] [Sears 1974] [Sears 1990] [Secco and Martins 2019] [Shirbhate et al. 2025] [Sibert 1943] [Sim and Curry 1985] [Sivells and Neely 1947] [Smith and Kroo 1990] [Tan and Plotkin 1986] [Uzun 2025] [von Kármán and Tsien 1945] [Wahler et al. 2025a] [Whitcomb 1940] [White 1963] [Wilmott 1986] [Wings and Winglets 1999] [Wu and Talmadge 1961] [Xieyuan 1985] [Yates 1974] [Yeh and Plotkin 1986] [Yu and Ansell 2023] [Yuan et al. 2018] [Zhou et al. 2020] [Zohar and Er-El 1988] [Zong et al. 2021]

Acoustic and aural detection of aircraft

Hearing, locating and classifying an aircraft from its sound, together with the radar, radio and visual detection literature that the same problem draws on. 90 of the 138 records date from 2015 or later.

The literature turned from the listener on the ground to the drone overhead. Of the 90 records from 2015 or later, 70 name an unmanned aircraft or a drone, while the period records concern ground observers, sound ranging and the aural and visual detectability of military aircraft, which is the inversion the review above describes.

138 records. [Abbott 2016] [Alexander and Kinzly 1979] [Alimadadi 2026] [Amanatiadis et al. 2017] [Aydın and Kızılay 2022] [Baldwin 1973a] [Baldwin and Frederickson 1966] [Barry and Magliozzi 1971] [Basak et al. 2022] [Bellucci 1963] [Bernardini et al. 2017] [Bishop and Tufariello 2019] [Blackburn and Joslin 2021] [Blanchard et al. 2020] [Brown et al. 2016] [Che Mamat and Abdul Aziz 2022] [Chen et al. 2015a] [Chew and Chapin 1963] [Cruzado et al. 2023] [Dafrallah and Akhloufi 2024] [de Macedo et al. 2025] [Dekoninck 2020] [Dingeldein et al. 1975] [Dolph et al. 2021] [Ernst and Sachau 2025] [Fang et al. 2023] [Fidell et al. 1990b] [Fidell et al. 1990a] [Forkun et al. 2020b] [Frederickson et al. 1967] [Gager et al. 1962] [Gaston et al. 2013] [Gayne 1965] [Ghenescu et al. 2026] [Go and Choi 2021] [Goldman 2016] [Gopalan et al. 2022] [Guvenc et al. 2017] [Guzik et al. 2019] [Haddad et al. 2019] [Han et al. 2024] [Harvey and O’Young 2016] [Harvey and O’Young 2018] [Hess 2012] [Highland et al. 2020] [Hilton et al. 1975d] [Hoff 1982] [Huang et al. 2026] [Jack et al. 2014] [JanakiRam 1980] [JanakiRam and Scruggs 1982] [Jekateryńczuk and Piotrowski 2025] [Jekateryńczuk et al. 2025] [Juřička and Juřičková 2020] [Kadyrov et al. 2022] [Kartashov et al. 2021] [Kim 2016] [Kim et al. 2025a] [Kletschkowski 2012] [Kloet et al. 2017] [Kocur et al. 2023] [Kozak 2021] [Kozeruk and Korzhik 2022] [Kozeruk and Korzhyk 2019] [Kumar S Rajanikanth 2024] [Kurdyla 1963] [Landers and Lacoss 1978] [Lee 2019] [Lee and Lee 2026] [Lim et al. 2025] [Liu et al. 2021] [Loewy 1963] [Loffi et al. 2021] [Ludeman 1979] [Manickam et al. 2020] [Marcus and Räf 2019] [Memorandum, US Reconnaissance Aircraft Reports Interception] [Michel 1989] [Minwalla et al. 2016a] [Minwalla et al. 2016b] [Moreland et al. 1965] [Morge-Rollet et al. 2022] [Mueller et al. 1993] [Muneer et al. 2026] [Muniraj and Farhood 2019] [Najafi et al. 2025] [Nemec et al. 2024] [Ogiso et al. 2019] [Oh et al. 2023] [Oleynikov et al. 2018] [Ollerhead 1971] [Pandat et al. 2025] [Paszkowski et al. 2024] [Poe and Arthur C. 1974] [Price and Hodge 1976] [Quaranta and Dimino 2007] [Rakesh and Reddy 2023] [Ramachandra 1979] [Rao Pittu et al. 2023] [Render and Jenkinson 1996] [Research on Control Takeover 2025] [Rizzi et al. 2017] [Rodenhiser et al. 2007] [Sahai et al. 2016] [Sahawneh et al. 2015] [Sahithi 2023] [Sanchez-Galan et al. 2025] [Scharine and Letowski 2013] [Schriever 1952] [Sedunov et al. 2018] [Sedunov et al. 2019] [Seidaliyeva et al. 2023] [Sesham et al. 2026] [Sheffield 2000] [Shelley 2018] [Shi et al. 2026] [Siegel and Crain 1960] [Siegel and Lanterman 1963] [Smith] [Stalnov et al. 2022] [Starr et al. 1975] [Sun et al. 2023b] [Svatos et al. 2021] [Tabassum and Bai 2022] [Thomason et al. 1967] [Tong et al. 2013] [Trinks and Haseborg 1982] [Uddin et al. 2021] [Verba et al. 2024] [Wallace and Vance 2019] [Wilson et al. 2021] [Wokoun 1962] [Woo et al. 2020] [Wright 1966] [Wu et al. 2021] [Yu 2011] [Zou et al. 2021] [Zu et al. 2017]

Unmanned aircraft design and operation

Unmanned aircraft design, operation and regulation, and the observation missions they now fly. 105 of the 111 records date from 2015 or later.

The mission that went unmanned has an almost wholly recent literature, which is the second half of the pattern the review above describes.

111 records. [Alieksieiev and Tsybov 2025] [Altman 2008] [An Overview on Unmanned 2017] [Barr et al. 2018] [Bauer and Nagy 2024] [Bookstaber 2000] [Cheng et al. 2025] [Choi 2020] [Choi et al. 2017] [Cieślak 2021] [Ciolponea 2022] [Combey et al. 2026] [Coombes et al. 2017] [Costello and Adams 2023] [De Luca et al. 2025] [Design and Fluid Flow 2015] [Ducard 2015] [Dudziak et al. 2020] [El Gaouti et al. 2024] [Elzoghby et al. 2017] [Evaluating the Use 2015] [Forkun et al. 2020a] [Fry 2008] [Fu et al. 2026] [Garcia and Eskandarian 2026] [Geng et al. 2024] [Ghofur et al. 2020] [Han and Barakos 2020] [Hartley et al. 2022] [Hashim 2020] [He et al. 2024] [Henderson 2023] [Henry et al. 2023] [Hrishikeshavan et al. 2015] [Irmawan and Eko Prasetiyo 2020] [Islam et al. 2015] [Jianhong and Yanxiang 2026] [Jimenez et al. 2016] [Jurczyk 2018] [Kaneko and Martins 2023] [Kang and Woolsey 2020] [Kant et al. 2023] [Kapnik 2019] [KeleŞ 2022] [Kim and Atkins 2022] [Kimathi and Lantos 2023] [Kistyarev and Wang 2025] [Kochuk et al. 2021] [Konert and Kasprzyk 2024] [Kopecki 2016] [Kumari and Raghunath 2016] [Leylek and Costello 2015] [Li 2019] [Lim et al. 2023b] [Lu et al. 2025] [Ma et al. 2024] [Macdonald and Schneider 2019] [Majka 2015] [Mark et al. 2019] [Marshall and Anderson 2015] [Mathur and Atkins 2023] [Matos and Marta 2024] [Matt et al. 2025] [Mihelič and Pozderec 2023] [Moore et al. 2022] [Mosov et al. 2020] [Multi-Rotors 2015] [Müller and Moormann 2023] [Nam and Joshi 2017] [Pande 2025] [Papa 2023] [Papageorgiou et al. 2018] [Papageorgiou et al. 2020] [Patterson et al. 2016] [Pecho et al. 2019] [Pentz and Tang 2017] [Pestana 2010] [Pham et al. 2025] [Pöysä et al. 2018] [Dhayalan et al. 2018] [Rhudy et al. 2023] [Rogalski 2018] [Ryan and Cummings 2016] [Scalea 2020] [Sudhakar et al. 2025] [Sabatini et al. 2015] [Santoso and Hariyanto 2022] [Sells and Crossley 2023] [Si et al. 2023] [Simmons et al. 2019] [Sun et al. 2019] [Tsuji 2024] [Unmanned and Uncontrolled 2015] [Venkataraman et al. 2017] [Venkataraman et al. 2019] [Vránics 2020] [Wan et al. 2019] [Wang et al. 2020a] [Winslow et al. 2018] [Wood et al. 2019] [Xu and Wang 2016] [Yu 2018] [Yuan 2026] [Yuma Proving Ground Az 2013] [Yuma Test Center Yuma Proving Ground AZ 2008] [Zhang 2026b] [Zhang 2026c] [Zhang et al. 2025c] [Zhou and Wang 2026] [Zhu and Duan 2015] [Żugaj 2017]

Engine exhaust noise and mufflers

Exhaust, intake and jet noise, and the mufflers and silencers that treat them, including muffler designs for engines other than aircraft engines. 8 of the 86 records date from 2015 or later.

86 records. [Ahuja and Bushell 1973] [Alfredson 1971] [Arseneau 1997] [Bender and Brammer 1973] [Bender and Brammer 1975] [Benzakein et al. 1973] [Buchwalder 1985] [Butzel 1982] [Casey 1984] [Chessell 1979] [Ciepluch 1973] [Czarnecki and Davis 1948] [Czarnigowski et al. 2019] [Dash et al. 2003] [Davis et al. 1953] [Doelling 1961] [Doelling and Bolt 1961b] [Doelling and Bolt 1961a] [Dyer 1956] [Emeric 1966] [Envia 2016] [Experimental Analysis of Exhaust 2017] [Ferrari and Castelli 1985] [Fischer 1992] [Fukuda 1960a] [Fukuda 1960b] [Fukuda 1963b] [Fukuda 1963a] [Gerber 2003] [Hargest 1972] [Hay 1971] [Hirschorn 1960] [Hoffman and Kennedy 1982] [Hosier 1976] [Hukuda 1962] [Hultgren 2015] [Jacques 1976] [Jaron et al. 2023] [Kaldschmidt et al. 1973] [Keast 1961] [Kenny 2004] [Kester 1974] [Knott 1974] [Ko 1971] [Kodres 2000] [Li et al. 2024b] [Lux and Landwehr 1980] [MacGregor et al. 1973] [Masuda 1996] [Matsushita and Suzuki 1984] [Morris et al. 1973] [Mutyala and Soedel 1974] [Nagao 1998] [Nassif 1969] [Nelson 1938] [Nelson et al. 2012] [Ohta 1935] [Pao 1971] [Patrick et al. 2000] [Pegg and Hilton 1974] [Pietrasanta and Galloway 1956] [Prasad and Crocker 1983] [Rhodes 1982] [Robinson 1979] [Samimy et al. 2003] [Samimy et al. 2004] [Semrau and Frye 1974] [Shaikn 1979] [Shivashankara 1978] [Shivashankara 1983] [Simcox et al. 1976] [Stephens 2010] [Stephens 2013] [Stokes and Davis 1953] [Tam 1987] [Tanaka et al. 1985] [Tarnow and Pommer 1988] [Taylor et al. 1973] [Thomson 1983] [Tyler and Towle 1955] [Veldman 1975] [Viswanathan 2018] [Wang 1981] [Wu 2010] [Yoshikawa 1992] [Yu and Huang 2018]

Loss of control, upset recovery, stall and spin

Loss of control in flight, upset prevention and recovery, stall, spin and envelope protection. 58 of the 80 records date from 2015 or later.

The literature the X-26A’s argument fed into is recent. The training requirement and the envelope protection described above both belong to the last decade of this cluster.

80 records. [Altunkaya et al. 2024] [Anderson 1985] [Autenrieb 2025] [Bihrle and Barnhart 1974] [Blanchard 1981] [Bottasso and Montinari 2015] [Bowman 1965] [Bromfield et al. 2023a] [Cano and Sobel 2016] [de Visser and Pool 2023] [Degtyarev et al. 2021] [Donaldson et al. 2012] [El Safany and Bromfield 2025] [Emami and Roudbari 2019] [Feistel et al. 1978] [Feistel et al. 1981a] [Gill et al. 2015] [Glīzde 2017] [Golovkin et al. 2019] [Gresham et al. 2024] [Hamza et al. 2022] [He et al. 2026a] [Healy 1958] [Hurley 1969] [Moguel 2015] [Johannes 1971] [Kao 1974] [Karpuk and Mosca 2024] [Lang et al. 2022] [Lang et al. 2025] [Ledegang and Groen 2015] [Lee et al. 2017a] [Lombaerts et al. 2017] [Ma and Chen 2023] [Ma et al. 2022b] [Malik et al. 2017] [Marcinkiewicz et al. 2019] [Milillo 1972] [Moreira et al. 2022] [Nabi et al. 2018] [Nelson 1974] [Campbell et al] [Campbell et al. 2021] [Pitts et al. 1974] [Rebont et al. 1977] [Roudbari and Saghafi 2016] [Ryffel et al. 2019] [Bainetov 2016] [Schuet et al. 2017] [Seo et al. 2019] [Shmelоv et al. 2019] [Siotia et al. 2026] [Smaili et al. 2018] [Sparks and Moerder 2002] [Srijayantha 1983] [Stough et al. 1987] [Taylor and Miller 1982] [Tong et al. 2023] [Van Baelen et al. 2020] [Van Dommelen 1995] [Wang et al. 2024a] [Wang et al. 2025a] [Wei et al. 2020] [White et al. 2021] [Woo et al. 2017] [Wu et al. 2020a] [Wu et al. 2020b] [Ye et al. 2015] [Yildiz et al. 2019] [Yin et al. 2019] [Yip et al. 1992] [Yu et al. 2020] [Yu et al. 2023] [Yue et al. 2025] [Zhang and Liu 2026] [Zhang et al. 2018a] [Zhang et al. 2021] [Zhao and Jim Zhu 2017] [Zheng et al. 2018] [Altunkaya et al. 2025]

Flight control, control allocation and fault tolerance

Flight control systems and laws, control allocation, fault tolerance and autopilots.

77 records. [Abdullina and Efanov 2020] [Almutairi and Aouf 2017] [Amitary and Jansen 2011] [Anderson and Innis 1965] [Anderson and Schroers 1972] [Banerjee 2019] [Bian et al. 2018] [Bolds-Moorehead et al. 2015] [Bowersox and Fan 2000] [Burken et al. 2006a] [Burken et al. 2006b] [Carithers and Montalvo 2018] [Chengtao et al. 2011] [Cochran 2015] [Coldsnow et al. 2009] [Cole et al. 2007] [Comer and Chakraborty 2024] [Cong et al. 2023] [Alesov 2021] [Craig 1965] [Curtiss 1971] [Demarchi and Haning 1978] [Dong et al. 2016a] [Dong et al. 2016b] [Dravid 1971] [Durand and Wasicko 1967] [Farajollahi and Markazi 2010] [Fasel 2002] [Flight Sciences Lab INC Buffalo NY 1964] [Gates and Schy 1951] [Grana and Shanks 1952] [Hamed 1993] [Hartmann et al. 1976] [Heidenreich 1947] [Hendrick 1977] [Li et al. 2023a] [Pearson and Jones 1976] [Herrmann and Ben-Asher 2016] [Hess 2018] [Hess and Peng 2018] [Jenney 1979] [Ji et al. 2023] [Jing and Ma 2025] [Kang and Choi 2022] [Kotitschke et al. 2026] [Lee 2023] [Lewis 1929] [Lewis 1930] [Liang et al. 2026] [Lu et al. 2017] [Lu et al. 2019] [Maughmer et al. 1990] [Mothes 2019] [Mueller et al. 2004] [Okumoto and Elsanker 1973] [Paulson and Shanks 1961b] [Persoon et al. 1980] [Powers and Sarrafian 1986] [Quagliarella and Iuliano 2017] [Rogers 2004] [Scordamaglia et al. 2025] [Sezgin et al. 2025] [Shang 2007] [Shi et al. 2023b] [Shmilovich and Princen 2026] [Strailman 1952] [Swaim 1970] [Swischuk and Allaire 2019] [Takeda 1970] [Vile et al. 2020] [Wagdi 1977] [Whitaker et al. 1977] [Wolowicz and Yancey 1973] [Xie et al. 2023b] [Xu et al. 2020] [Yang and Gao 2020] [Zhang et al]

Aerodynamics, airfoils and aerodynamic design

Airfoils, boundary layers, high-lift and laminar flow, computational aerodynamics and aerodynamic design.

68 records. [Addessio and Skifstad 1975] [Akbar 2020] [Atkin 2001] [Bayındırlı 2025] [Bernot 1979] [Bishara et al. 2018] [Borodulin et al. 2017] [Bright et al. 2013] [Calvert 1950] [Chaudhuri 1977] [Chernyshev et al. 2019] [Coder and Somers 2020] [Collier et al. 1990] [Cordner 1967] [Corson 1941] [Drakin 1963] [Englar 1970] [Fejtek 1993] [Gardner and Downey 1950] [Graham et al. 1945] [Greenhalgh 1983] [Greer et al. 1999] [Greer et al. 2000] [Hansmann and Stumpf 2026] [Head and Hohenemser 1951] [High-Fidelity Aerodynamic Models 2015] [Human-Powered Aircraft Wing Design 2014] [Introduction to Aircraft Aerodynamic 2021] [Jones 1964] [Katz and Maskew 1988] [Kaul 2024] [Keller 2019] [khan and Padhy 2019] [Kubrynski 1999] [Lamar et al. 1981] [Lange and Gieseler 1953] [Larrabee 1975] [Lindstrom et al. 1970] [Livescu 2016] [Matheson 1987] [May and Widdison 1971] [Meyer and Jiran 1981] [Mokhtari et al. 2020] [Murillo and McMasters 1984] [NACA Conference on High-Speed 1958] [Nie et al. 2025] [Obayashi 1999] [Olson 2015] [Otsuka et al. 2017] [Pivko 1956] [Quick 1937] [Roy 2009] [Schlichting 1939] [Shindo and Joppa 1980] [Sidhu 2023] [Tai 1993] [Tanaka et al. 2024] [Tokugawa et al. 2026] [Vaughn et al. 2008] [Wang 1980] [Wang 2026] [Williams and Howe 1970] [Wing Design Considerations 2021] [Yang] [Yih et al. 1952] [Zhang 2026a] [Zhang et al. 2015] [Zhu et al. 2023a]

Airframe noise, cabin noise and vibration

Noise from the airframe itself, noise and vibration inside the aircraft, and the paths between them.

63 records. [Bishop 1961] [Bolds 1961] [Bolds 1962] [Burley 1974] [Choudhari et al. 2011] [Clarkson and Mead 1973] [Dalan and Cohen 1985] [Dobrzynski 1981] [Doherty and Butzel 1979b] [Doherty and Butzel 1979a] [Douglas Aircraft Co Long Beach Ca 1963] [Elkoby et al. 2007] [Esnault] [Fink 1979] [Fink and Schlinker 1980] [Ford 2004] [Grosveld 1985] [Grosveld 1988] [Grosveld et al. 1980] [Heitman and Mixson 1986] [Heller and Dobrzynski 1977] [Howe 1978] [Howe 1981] [Howe 1999] [Howlett 1979] [Humphreys et al. 2016] [Hutchins 1972] [Kholodar 2016] [Khorrami et al. 2009] [Kuantama et al. 2019] [Kuhn 1975] [Landmann et al. 1989] [Langer and Blech 2019] [Lauchle and Park 2002] [Lockard et al. 2008] [Mayes and Edge 1962] [Mixson et al. 1977] [Morgan and Hardin 1975] [Probst et al. 2017] [Ravetta et al. 2019] [Ride Quality of Crew-Manned 1975] [Shaw et al. 1988] [Sikora and Mendenhall 1974] [Simpson 1990] [Soovere 1982] [Soovere 1985] [Strelkov and Kharlamov 1967] [Takahashi et al. 2023] [The Measurement and Analysis 1976] [Thomas 1961a] [Thomas 1961b] [Townsend 1966] [Turkdogru Gurun et al. 2021] [Unruh 1981] [Unruh et al. 2002] [Vaicaitis 1980] [Vaicaitis and Mixson 1985] [Wanglomklang et al. 2025] [Wilby 1982] [Williams 2002] [Winter 2023] [Yamamoto et al. 2023] [Zheng 2021]

Surveillance, reconnaissance and observation

Surveillance, reconnaissance and night observation aircraft, manned and unmanned, and their sensors.

56 records. [Abich et al. 2016] [Amelin 2022] [Anderson 1976] [Bailey and McClintic 1974] [Beech Aircraft Corp Wichita Ks 1966] [Bell Aerospace Co Buffalo Ny 1955a] [Bell Aerospace Co Buffalo Ny 1955b] [Bell Aerospace Co Buffalo Ny 1957] [Belsky 2022] [Blosser 1952] [Blosser 1953] [Bracken and Grotte 1979] [Bucklew 2009] [Clark 2013] [Cornell Aeronautical Lab INC Buffalo NY 1971b] [Cornell Aeronautical Lab INC Buffalo NY 1971c] [Cornell Aeronautical Lab INC Buffalo NY 1971a] [Dunnavan 1983] [Fisher et al. 1956] [Forsythe, A.C.R. 1946] [Frazier 2016] [Hasan et al. 2018] [Henderson 1978] [High Altitude Reconnaissance Aircraft 1989] [Hinds and Shames 1975] [Holley and Irving B. 1946] [Hoppes et al. 1964] [Huang et al. 2018] [Januszewska and Pringle 2021] [Kisabo et al. 2017] [Koper 1976] [Kumar 1997] [Leahy et al. 2015] [Lempert 1975] [Lowrance and Smith 1996] [Mack 2003] [McQUILLEN and Huang 1971] [Meullen et al. 1956] [Olsen et al. 2019] [Quirion and Liu 2020] [Rader 1989] [Reconnaissance and Auxiliary Aircraft 2008] [Republic Aviation Corp Mineola Ny 1963] [Rexcharles Enyinna Donatus et al. 2026] [Rutherford and Crowder 1958] [Sakthivel and Venkatesan 2017] [Schutz and Kutrzyba 2000] [Setiawan et al. 2026] [SlEWERT and Stewart 1967] [Stottier 1995] [Tittel 2010] [Uhl 2003] [Whittingham and Swan 1960] [Widger 1963] [Yazdi 1991] [Zhen 2019]

Electric, hybrid-electric and solar-powered aircraft

Electric, hybrid-electric, solar and fuel cell propulsion, where a title names no other cluster’s subject. 42 of the 47 records date from 2015 or later.

47 records. [Kolluri et al. 2021] [Kuwamura and Hara 2017] [Phung et al. 2024] [Rohacs and Rohacs 2019] [Scholz et al. 2023] [Simmons et al] [Binghua et al. 2021] [Brinza et al. 2026] [Buckley et al. 2020] [Cahn et al. 1966] [Abubakar Tatari Ali Polytechnic and Danjuma 2022] [Danjuma et al. 2021] [Development and Application 2025] [Doyle 2020] [Dr. Olivia Davis 2021] [Figueira et al. 2025] [Finger et al. 2020b] [Gong 2024] [Green 1931] [Hace 2019] [Hoelzen et al. 2018] [Hu et al. 2026b] [In-Flight Testing into Atmospheric 2025] [Isikveren 2018] [Kellermann et al. 2020] [Likhite 2022] [Lim et al. 2023a] [Lobitz et al. 2023] [Mukhachev et al. 2022] [Nasoulis et al. 2022] [Ogawa et al. 2015] [Palaia et al. 2023] [Pornet and Isikveren 2015] [Prasannakumar et al. 2024] [Reid et al. 2024] [Reiquam 1982] [Riboldi 2018] [Staats et al. 2025] [Schnulo et al] [Tarhan et al. 2021] [Tuck et al. 2018] [Wahler et al. 2025b] [Wall and Meyer 2020] [Wen et al. 2023] [Yang et al. 2019] [Zhu et al. 2016] [Жданов and Зінченко 2015]

Flight dynamics, stability and simulation models

Flight dynamics models, longitudinal and dynamic stability, simulation and the response to turbulence.

35 records. [Abhishek and Prasad 2016] [Abzug and DaRos 1955] [An Introduction 1966] [Antipov 2020] [Aziz and Loya 2025] [Barnes and Yager 1985] [Beeman 1972] [Beyers 1983] [Beyers 1988] [Churchill and Dugan 1982] [Ferguson and Thomson 2015] [Ferguson et al. 1984] [Grantham et al. 1974] [Grubin 1972] [Gupta et al. 2016] [Hacker and Wroblewski 2009] [Hitzel and Zimper 2018] [Houbolt 1971] [Houck et al. 1977] [Juhasz et al. 2021] [Metodiev 2025] [Montalvo and Costello 2015] [Moul and Brown 1959] [Nagabhushan 1983] [Oruc et al. 2017] [Phillips 1975] [Reid 1978] [Rodgers 1966] [Shayak et al. 2024] [Steiner and Pratt 1967] [Thelander 1965] [Thorson and Bohne 1960] [Trevino 1986] [Yuan et al. 2019] [Yuan et al. 2020]

Other aeronautical literature

The residual, reported and not hidden. Records about a whole aircraft that belong to no other cluster in the table, including configuration and design studies, air data, test capability and the hazards of low-level operation.

It holds 0.8 percent of the survey and is heterogeneous, with no family in it large enough to name as a literature of its own.

30 records. [Abdukayumov 2022] [Air Force Test Pilot School Edwards Afb Ca 1994b] [Bailey et al. 1996] [Bevilaqua 2021] [Bryant 1963] [Carico 1995] [Coiro and Nicolosi 2001] [Continental Army Command Fort Monroe VA 1958] [Dynamic Response Analysis 2021] [Engblom et al. 2016] [Ericsson 1987] [Finch and Matranga 1959] [Forehand and Bair 1969] [General Aviation Aircraft Design 2022] [Graves 1982] [Guidry et al. 2001] [High-Speed Water-Based Aircraft 1953] [Hightower 1985] [Hom et al. 1983] [Ivanković et al. 2023] [Kristl et al. 1999] [Miller et al. 1983] [Murphy et al. 2019] [Nam and Mavris 2018] [Petrescu et al. 2017] [Ralles 1966] [Smith and Bernier 1966] [Thompson 2014] [Wild 1966] [Zhu et al. 2023b]

Wind tunnels, models and test technique

Wind tunnels, their control and corrections, and model test technique.

26 records. [Anderson 1968] [Bamber 1961] [Billingsley 1976] [Bliss 1980] [Boswell 1970] [Butler 1976b] [Cook 1964] [Czysz 1963] [Diggins 1951] [Dowell and Bliss 1978] [Emslie 1966] [Feistel et al. 1981b] [Hoehne 1967] [Hunton and Harry 1948] [Kashitani et al. 2019] [Kilgore and Averett 1964] [Mennell 1975] [Muhlstein and Coe 1979] [Nicolaides 1971] [Petty 1975] [Rittenhouse 1959] [Stallings and Hartman 1981] [Wallace 1952] [Whittley and Garland 1961] [Wind Tunnel Balance 1974] [Winther et al. 1981]

Rotorcraft and vertical lift flight mechanics

Helicopter, tilt-rotor and other vertical lift flight mechanics, hover and their test facilities, where a title names no other cluster’s subject.

19 records. [Baisley 1973] [Castles and Durham 1956] [Cox and Abbott 1966] [Csencsitz et al. 1973] [Culpepper and Murphy 1979] [Durbin and McGeer 1982] [Edenborough 1968] [Ham and Young 1966] [Heyson 1980] [Johnson 1970] [Kelley et al. 1986] [Magee and Taylor 1971a] [Olson 1978] [Reader 1976] [Reilly 1970] [Sherman and Warburton 1993] [Swaim 1969] [Triantafyllou and Geyer 2014] [Zhang and Xia 2017]

Where the Framing Breaks Down

Treating this as one aircraft is a convenience of the designation system and not a fact. The X-26A and the X-26B share an airframe and share nothing else. They had different customers, different missions and different decades of relevance. An article organised around the shared lift-to-drag ratio is making an argument, and the reader should know it is an argument.

The unifying claim is real but it is not a claim about intent. No source consulted says that anyone at the Naval Test Pilot School chose the SGS 2-32 because its aspect ratio implied a low power requirement, or that anyone at Lockheed chose it because its wing produced instructive adverse yaw. Each programme chose it for its own reason and the common cause is visible only in retrospect. The article derives the connection and does not assert that anyone at the time saw it.

Neither airframe was designed for its role and neither aircraft answered an aerodynamic unknown, which is close to the finding the previous article made about the X-25, for which no aerodynamic result is recorded. Two consecutive designations went to existing civil designs acquired for their properties, the X-25 trainers in modified form. That is evidence about the designation system, and it belongs with the rest of it in the closing article of this series. The vehicle-by-vehicle record for the series generally is Jenkins, Landis and Miller on the American X-vehicles.

Finally, the three lost airframes are unexplained here. Three of four X-26As were destroyed and replaced. A docile sailplane operated by an organisation of professional test pilots should not have that record, and this article does not know why it does. It is left as an open question, because the obvious inference, that an aircraft used to demonstrate departures will occasionally depart, is the kind of plausible reasoning that should not be presented as fact.

The Source Base

The aircraft has almost no technical literature. Of the 3,576 research records in this article’s references, seven carry the X-26, Schweizer, the SGS, the QT-2, the Q-Star or the YO-3 in their titles, and none is about either X-26. Two concern a different Schweizer sailplane, the SGS 1-36, in a National Aeronautics and Space Administration flutter clearance and a study of its flight at very high angles of attack, in Kehoe and Ellison 1985 and Sim 1990. One names the Q-Star as an experimental quiet aircraft, in Griffith 1971. The other four concern the YO-3A, which is the QT-2’s operational descendant. The Army’s preliminary evaluation of the YO-3A is the only evaluation of the type in its operational role among them, in Condon et al. 1970, and the remaining three come from the later research use of the aircraft, a measurement of its propeller thrust and torque in Ormsbee et al. 1977 and its work as an acoustic research aircraft in Cross and Watts 1983 and Cross 1984. The specifications come from sailplane references and museum material, and the operational detail from historical accounts rather than from test reports.

That is a property of the procurement. An aircraft taken from an existing design for properties it already has generates little development literature, because the development was confined to modification, which for the QT-2 airframes meant the thicker wings and spars that Historic Aircraft 2017 reports, and the X-25 is the same case.

The supporting physics is abundant on one side and thinner on the other. Lateral control and adverse yaw are extremely well documented once the period’s own vocabulary is used, in the cluster on lateral control, ailerons and adverse yaw, and the propeller-noise and propagation literature is substantial. 75 of that cluster’s 181 records date from before 1970, and its titles are phrased in terms of ailerons, spoilers, rudders, rolling and yawing moment and lateral control, while the count under Thin Subjects shows how rarely a title uses the bare term adverse yaw.

The research survey holds 3,576 research records drawn from Crossref, the National Aeronautics and Space Administration’s Technical Reports Server and the Defense Technical Information Center, of which 1,090 are report primaries, being 30.5 percent, by the identifier rule set out under The Definition of Primary. The median publication year is 2002. Of the 3,534 dated records, 694 were published in 1971 or earlier, by which year the YO-3A had finished operating in Vietnam, being 19.6 percent, and 1,558 were published in 2015 or later, being 44.1 percent.

The Definition of Primary

Primacy is a property of the document, and this survey derives it from the identifier. A record is a report primary when its address is on the National Aeronautics and Space Administration’s Technical Reports Server or it carries a digital object identifier under the 10.21236 prefix, which Crossref registers for Defense Technical Information Center reports. The period reports on lateral control, propeller noise and sound propagation that carry this article’s argument are report primaries under that rule, and so are the Army’s evaluation of the YO-3A, the YO-3A propeller study and the YO-3A systems manual. The rule does not reach the journal and conference papers among the first-hand sources, such as the in-flight acoustic test technique of the YO-3A and the papers on atmospheric absorption in the Journal of the Acoustical Society of America, so 30.5 percent is a lower bound on how much of the survey is first-hand.

Thin Subjects

Seven subjects that this article’s derivations depend on have thin literatures. Each count below is the number of research records in this survey whose title carries at least one of the listed terms, with a hyphen read as a space.

Subject	Title terms counted	Records
Adverse yaw named as such	adverse yaw, proverse yaw	7
The glide ratio, best glide and minimum sink	glide ratio, best glide, glide performance, gliding performance, minimum sink, sink rate, sinking speed, sink speed, speed polar, glide speed	16
Power required and the minimum-power speed	power required, minimum power, maximum endurance	13
The test pilot schools	test pilot school, test pilot schools	12
The transfer of training from one device to another	transfer of training, training transfer, transfer effectiveness, quasi transfer	6
Hearing an aircraft, its audibility and aural detection	aural, audibility, audible, nondetectability, non detectability	15
The ambient noise and masking that set a detection threshold	ambient noise, background noise, ambient acoustic, ambient soundscape, masking, masker	10

Adverse yaw is documented under other names. Seven titles name adverse or proverse yaw, one of them from before 2017, while the lateral control cluster holds 181 records on ailerons, rolling and yawing moments and lateral control, so the X-26A’s lesson rests on the period’s vocabulary rather than on its own name.

Glide performance is carried by the sailplane literature rather than named. Of the 16 titles that name a glide ratio, best glide or sink rate, one names a sailplane, and the sailplane cluster holds 178 records.

Power required has almost no period literature under its own name. Thirteen titles name power required, a minimum-power speed or maximum endurance, and one of them dates from before 2000, so the distinction between best glide and minimum power rests on the standard performance relation derived above, which the performance cluster treats inside range, endurance and drag.

The test pilot schools are described rather than studied. Twelve titles name a test pilot school, one of them the Naval Test Pilot School, and none names a sailplane.

The X-26A’s central claim has no direct literature. Six titles name the transfer of training, all six of them from 2015 or later and all concerning simulators or virtual reality, and none compares a sailplane with another device.

Detection by ear was a period subject. Of the 15 titles that name hearing an aircraft, its audibility or aural detection, six date from before 1980, and the later ones concern noise contours, prediction codes, rotorcraft and cockpit alerts.

The ambient threshold is rarely the subject of a title. Ten titles name ambient noise, background noise or masking, and four of them concern detection, while the rest concern annoyance and perception.

What the Survey Admits

A record is admitted only when a person reading its title finds it on this article’s subject. The subject is the aircraft, manned or unmanned, and its flight, performance, stability, control, flight test and noise, together with the propagation and detection of sound in the atmosphere and the training and safety of the people who fly. Many words this subject depends on also name something else, and a record that shares only such a word is excluded. Glider also names the ocean glider, a gliding mammal and a mathematical object, and soaring also appears as a figure of speech in politics and literature. Propeller also names the ship’s propeller and the ventilation fan, rudder also names a ship’s rudder and several artists, and aileron also names a pharmaceutical company. Upset also names single-event upset in electronic memory, startle also names the startle response in clinical and animal research, aspect ratio also names a property of honeycomb cores and roughness elements, and noise also names noise in the radar and radio sense. Audibility is also a question of alarms, sirens, train horns and dwellings, and detection also belongs to seismology and to explosives screening. A neutral title on propeller theory or blade stress that appears in the Journal of Ship Research or International Shipbuilding Progress is treated as marine work and excluded. Satellites, spacecraft attitude, ballistic projectiles, ballistic re-entry bodies and launch vehicles are excluded, and so are unmanned aircraft used only as instruments for another discipline, such as crop, peatland and rock-wall surveys. The winged space shuttle orbiter is kept for its gliding flight. Correction notices, peer-review records, figure records, encyclopedia and dictionary entries, standards and recommended practices, and news items are excluded as well, because a survey counts research works. A signed comment on a paper, a discussion of a paper, the author’s reply and a signed letter on a research subject argue about a result and are research works, so they are kept when their subject is this article’s, while an unsigned discussion record is not. Book reviews are not admitted either, and nor is a second deposit of a document already held, such as a report-server copy of a meeting paper whose own record is kept, because counting it would count one work twice. The residual cluster admits a record only when its title concerns a whole aircraft’s configuration, design, flight or operation and no named cluster fits it, and a record whose only link to this article is the aircraft as a structure, its landing gear and tyres, ground equipment, maintenance or law is excluded.

Some records of doubtful relevance are kept. Muffler designs for engines other than aircraft engines are kept, because the acoustics of an exhaust silencer does not depend on the vehicle. Unmanned aircraft flown as observers of wildlife, fire, roads and the sea are kept, because persistent low-altitude observation is the mission the X-26B’s line carried. Missile wing aerodynamics, aircraft weather reconnaissance, the flight mechanics of birds, and law on unmanned aircraft are kept, because each shares this subject’s physics or its mission, and a reader may weigh each accordingly.

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, from the public record. The X-26A is an unmodified Schweizer SGS 2-32 operated by the United States Naval Test Pilot School for flying-qualities instruction. Four were ordered and three were lost and replaced. Two airframes, serials 67-15345 and 67-15346, were converted by Lockheed Missiles and Space Company to QT-2 and QT-2PC configuration with a Continental O-200 of 100 horsepower driving a four-blade propeller through an extension shaft. Two aircraft arrived at Soc Trang on 22 January 1968 and flew 591 hours of night surveillance between 24 January and 24 March 1968. The Army specification to which the YO-3A was designed called for acoustic undetectability at 1,500 feet, the aircraft was first heard at 750 in passes over the airfield, and missions were flown no lower than 800. The aircraft returned in 1969 and were redesignated X-26B. The work continued through the Q-Star to the YO-3A, which operated in Vietnam during 1970 and 1971, although the accounts disagree on how many were built and when operations began.

Engineering analysis, derived here and checkable. That adverse yaw is proportional to lift coefficient follows from the classical elliptic-loading result. That the observability index scales as wing loading times span over the cube of speed and the directional stiffness, with the helix angle cancelling, is algebra. The 6.02 decibels per doubling of range is exact for spherical spreading. The statement that the QT-2PC fell one doubling short of the 1,500 foot figure follows from the two reported distances alone.

Assumed, and marked as such throughout. The Oswald efficiency of 0.90 and zero-lift drag coefficient of 0.012. Every quantity describing the comparison jet trainer. The helix angles and directional stiffnesses of both aircraft. The QT-2PC gross weight of 2,400 pounds and its lift-to-drag ratio of 20. The 40 dBA night ambient. The propeller diameters and speeds. None of these is a measurement of an X-26.

Inference, and labelled as inference. That the two programmes selected the same airframe for reasons traceable to a single property is an inference drawn here, not a documented rationale, as Where the Framing Breaks Down acknowledges. That the acoustic limit moved to the exhaust and airframe once the propeller was slowed follows from the tip-speed arithmetic being far larger than the shortfall, but no source consulted states which term dominated.

What the record does not settle. Why three of four X-26A airframes were lost. The QT-2PC’s actual gross weight, which the accounts give as 2,182 and 2,500 pounds, its drag polar, and its propeller geometry beyond the 100 inch diameter. What the measured sound level was at any stated distance, as opposed to the detection distance. Whether the 1,500 foot specification was met under defined conditions, although the YO-3A is reported to have operated silently at 1,000 feet or lower depending on background noise. How long the X-26A will remain in service, since the Navy still lists two in the inventory and gives no retirement date.

Written from current knowledge. The contemporary survey postdates the editorial date of this article.

Out of Scope

The sensor packages the QT-2PC and YO-3A carried, including low-light television and infrared. The tactical conduct of night observation operations. The Schweizer company history and the American soaring movement. Sailplane structural design and certification. Psychoacoustics and the perception of aircraft noise, as distinct from its physical propagation. The YO-3A’s own programme, which deserves its own treatment. Modern active noise control.

Conclusion

The Schweizer X-26 is one airframe, two aircraft, and a single number.

A high lift-to-drag ratio requires a long slender wing, and a long slender wing flown slowly produces adverse yaw four and a half times larger than a jet’s and seventeen times slower. Those two factors made the aircraft a teaching tool for the Naval Test Pilot School. The same high lift-to-drag ratio means the aircraft needs twenty-four horsepower of the hundred it carries, so Lockheed could throttle the engine, bury it in mufflers, and turn a large propeller slowly enough to be inaudible beyond 750 feet.

The two programmes wanted opposite things and both got them from the same property. One wanted a fault made visible. The other wanted an aircraft made absent.

Neither airframe was designed for its role. Both came from a production sailplane that its manufacturer had already optimised for unrelated reasons. This series has now found that twice in succession, and the pattern is evidence about the designation system rather than about aeroplanes.

The next article in this series takes up the Lockheed X-27.

Equations

This section collects the 39 display equations of the article in the order they appear, each under its number and reproduced exactly as it stands in the text. A title in bold names an established result, and a title in italics beginning with the word Bespoke names a construction made for this analysis. Of the 39, 29 are established and 10 are bespoke. Aerodynamic quantities are in United States customary units, with weight in pounds, area in square feet, speed in feet per second or miles per hour as each line states and density in slugs per cubic foot at sea level, sound levels are in decibels with pressure ratios taking twenty times the logarithm and power ratios ten, and the Oswald efficiency of 0.90, the zero-lift drag coefficient of 0.012, the QT-2PC weight of 2,400 pounds and its lift-to-drag ratio of 20 are values the article assumes.

Equation 1, Maximum Lift-to-Drag Ratio of a Parabolic Polar. For a parabolic polar the maximum lift-to-drag ratio is half the square root of pi times Oswald efficiency times aspect ratio over the zero-lift drag coefficient.

\[\left( \frac{L}{D} \right)_{max} = \frac{1}{2} \sqrt{\frac{\pi e A}{C_{D_0}}} \tag{1}\]

Equation 2, Parabolic Drag Polar. The drag coefficient of a wing is a zero-lift term plus an induced term proportional to the square of the lift coefficient and inversely proportional to aspect ratio.

\[C_D = C_{D_0} + \frac{C_L^2}{\pi e A} \tag{2}\]

Equation 3, Lift Coefficient for Maximum Lift-to-Drag Ratio. The lift-to-drag ratio is greatest where the induced and zero-lift drag terms are equal, which fixes the best-glide lift coefficient.

\[\frac{C_L^2}{\pi e A} = C_{D_0} \quad \Longrightarrow \quad C_L^{\ast} = \sqrt{\pi e A \, C_{D_0}} \tag{3}\]

Equation 4, Aspect Ratio of the X-26A Wing. The documented span of 57.125 feet over the wing area of 180 square feet gives an aspect ratio of about 18.1.

\[A = \frac{b^2}{S} = \frac{(57.125)^2}{180} = 18.1 \tag{4}\]

Equation 5, Bespoke Maximum Lift-to-Drag Ratio of the X-26A. With an Oswald efficiency the article assumes as 0.90 and a zero-lift drag coefficient it assumes as 0.012, the relation gives about 32.7 against a quoted 35.

\[\left( \frac{L}{D} \right)_{max} = \frac{1}{2} \sqrt{\frac{\pi (0.90)(18.1)}{0.012}} = 32.7 \tag{5}\]

Equation 6, Bespoke Best-Glide Lift Coefficient of the X-26A. The same assumed efficiency and zero-lift drag give a best-glide lift coefficient of about 0.78.

\[C_L^{\ast} = \sqrt{\pi (0.90)(18.1)(0.012)} = 0.784 \tag{6}\]

Equation 7, Bespoke Best-Glide Speed at Two Wing Loadings. The lift balance at the assumed best-glide lift coefficient and sea-level density gives about 63 miles per hour at the gross wing loading of 7.94 and about 55 at the quoted 6.0 pounds per square foot. Schweizer SGS 2-32

Equation 8, Incidence Change from Rolling. A wing section at spanwise station $y$ on an aeroplane rolling at rate $p$ meets the flow at an incidence changed by the local vertical velocity over the airspeed.

\[\Delta \alpha = \frac{p \, y}{V} \tag{8}\]

Equation 9, Yawing Moment due to Roll Rate of an Elliptic Wing. Integrating the induced drag asymmetry across an elliptically loaded span gives the classical yawing moment derivative of minus one eighth of the lift coefficient.

\[C_{n_p} = -\frac{C_L}{8} \tag{9}\]

Equation 10, Lift Coefficient from Wing Loading and Speed. The lift coefficient in level flight is twice the wing loading over density times the square of speed, so it rises as the aeroplane slows.

\[C_L = \frac{2 (W/S)}{\rho V^2} \tag{10}\]

Equation 11, Yawing Moment Coefficient in a Steady Roll. In a steady roll the yawing moment coefficient is the yaw-due-to-roll derivative times the helix angle.

\[C_n = C_{n_p} \cdot \frac{pb}{2V} \tag{11}\]

Equation 12, Sideslip Driven Against Directional Stiffness. To first order the sideslip that the adverse yawing moment drives is that moment over the directional stiffness derivative.

\[\beta \approx \frac{|C_n|}{C_{n_\beta}} \tag{12}\]

Equation 13, Steady Roll Balance and Helix Angle. In a steady roll the aileron moment balances the roll damping moment, so the helix angle is fixed by aileron power and roll damping alone.

\[C_{l_{\delta_a}} \delta_a + C_{l_p} \frac{pb}{2V} = 0 \quad \Longrightarrow \quad \frac{pb}{2V} = -\frac{C_{l_{\delta_a}} \delta_a}{C_{l_p}} \tag{13}\]

Equation 14, Roll Rate from the Helix Angle. The roll rate is the helix angle times twice the airspeed over the span, so a long wing rolls slowly.

\[p = \frac{pb}{2V} \cdot \frac{2V}{b} \tag{14}\]

Equation 15, Time to Reach a Bank Angle. At a steady roll rate the time to reach a bank angle is that angle over the roll rate, written through the helix angle.

\[t = \frac{\phi}{p} = \frac{\phi \, b}{2 V \left( pb/2V \right)} \tag{15}\]

Equation 16, Bespoke Observability Scaling of Adverse Yaw. The article multiplies sideslip by time to bank as an index of how observable adverse yaw is and finds it scales as wing loading times span over the cube of speed and the directional stiffness.

\[\beta \, t \propto \frac{(W/S) \, b}{V^3 C_{n_\beta}} \tag{16}\]

Equation 17, Stall Speed. The stall speed is the speed at which the lift balance requires the maximum lift coefficient.

\[V_{stall} = \sqrt{\frac{2 (W/S)}{\rho \, C_{L_{max}}}} \tag{17}\]

Equation 18, Maximum Lift Coefficient Implied by the Quoted Stall. Inverting the stall relation at the quoted 46 mile per hour stall and the quoted wing loading of 6.0 pounds per square foot gives a maximum lift coefficient of about 1.11.

\[C_{L_{max}} = \frac{2 (W/S)}{\rho V_{stall}^2} = 1.11 \tag{18}\]

Equation 19, Bespoke Stall Margin and Sideslip Growth at the Training Speed. At a training speed the article takes as 60 miles per hour, the aircraft flies thirty percent above the stall and the sideslip at the stall would be seventy percent larger.

\[\frac{V}{V_{stall}} = \frac{60}{46} = 1.30, \qquad \frac{\beta_{stall}}{\beta_{60}} = \left( \frac{60}{46} \right)^2 = 1.70 \tag{19}\]

Equation 20, Power Required for Steady Flight. The power required for steady flight is weight times speed over the lift-to-drag ratio.

\[P = \frac{W V}{L/D} \tag{20}\]

Equation 21, Bespoke Power Required by the QT-2PC. At an assumed weight of 2,400 pounds, an assumed lift-to-drag ratio of 20 and 110 feet per second, the power required is about 24 horsepower.

\[P = \frac{(2400)(110 \, \text{ft/s})}{20} = 13{,}200 \, \text{ft lb/s} = 24 \, \text{hp} \tag{21}\]

Equation 22, Power Required Against Speed. The power required is a parasite term rising as the cube of speed plus an induced term falling inversely with speed.

\[P = \tfrac{1}{2} \rho V^3 S \, C_{D_0} + \frac{2 W^2}{\rho V S \pi e A} \tag{22}\]

Equation 23, Minimum Power Condition. At minimum power the parasite term is three times the induced term, which raises the lift coefficient by the square root of three and lowers the speed by the fourth root of three.

\[C_{L, mp} = \sqrt{3} \, C_L^{\ast}, \qquad V_{mp} = \frac{V_{bg}}{3^{1/4}} = 0.760 \, V_{bg}, \qquad \left( \frac{L}{D} \right)_{mp} = \frac{\sqrt{3}}{2} \left( \frac{L}{D} \right)_{max} \tag{23}\]

Equation 24, Ratio of Minimum Power to Best-Glide Power. Power at the minimum-power speed is about 0.88 of the power at best glide.

\[\frac{P_{mp}}{P_{bg}} = \frac{0.760}{0.866} = 0.877 \tag{24}\]

Equation 25, Bespoke Noise Value of Flying at Minimum Power. If radiated sound power followed shaft power, an assumption the article adopts to bound the effect, the saving at minimum power would be worth about half a decibel.

\[10 \log_{10} \frac{1}{0.877} = 0.57 \text{ dB} \tag{25}\]

Equation 26, Sound Pressure Level. Sound pressure level is twenty times the logarithm of the pressure ratio to a reference of 20 micropascals.

\[\text{SPL} = 20 \log_{10} \frac{p}{p_{ref}}, \qquad p_{ref} = 20 \, \mu\text{Pa} \tag{26}\]

Equation 27, Spherical Spreading of Intensity. Intensity from a compact source of acoustic power $W_{ac}$ falls as the inverse square of range over the surface of a sphere.

\[I = \frac{W_{ac}}{4 \pi r^2} \tag{27}\]

Equation 28, Spherical Spreading Loss with Distance. The sound pressure level falls by twenty times the logarithm of the range ratio, 6.02 decibels for every doubling. Beranek on noise and vibration control Pierce on acoustics

\[\text{SPL}(r) = \text{SPL}(r_0) - 20 \log_{10} \frac{r}{r_0} \tag{28}\]

Equation 29, Bespoke Maximum Audible Range. Taking the aircraft as audible until the spreading level falls to the ambient, the maximum range follows from the source level at a reference range.

\[r_{max} = r_0 \cdot 10^{\, (\text{SPL}(r_0) - L_{amb}) / 20} \tag{29}\]

Equation 30, Slant Range. The slant range is the hypotenuse of the altitude and the horizontal distance.

\[r = \sqrt{h^2 + x^2} \tag{30}\]

Equation 31, Bespoke Detection Range Change with Ambient Level. Within the article’s detection criterion a five decibel fall in ambient lengthens the detection range by a factor of 1.78.

\[\frac{r_{max}(L_{amb} - \Delta L_{amb})}{r_{max}(L_{amb})} = 10^{\Delta L_{amb}/20} = 10^{5/20} = 1.78 \tag{31}\]

Equation 32, Blade Passing Frequency. The fundamental tone of a propeller is the blade count times the revolutions per minute over sixty.

\[f = \frac{N_b \, \text{rpm}}{60} \tag{32}\]

Equation 33, Atmospheric Absorption Loss. Absorption loss accumulates linearly with distance at a coefficient that rises steeply with frequency.

\[L_{abs} = \alpha \, r \tag{33}\]

Equation 34, Propeller Tip Speed. The rotational tip speed is pi times the diameter times the revolutions per minute over sixty.

\[V_{tip} = \frac{\pi D \, \text{rpm}}{60} \tag{34}\]

Equation 35, Advance Ratio. The advance ratio is forward speed over the product of rotational speed in revolutions per second and diameter.

\[J = \frac{V}{n D} \tag{35}\]

Equation 36, Tip Mach Number. The tip Mach number is the tip speed over the speed of sound.

\[M_{tip} = \frac{V_{tip}}{a} \tag{36}\]

Equation 37, Incoherent Sum of Sound Levels. Independent sources add in power, so the total level is ten times the logarithm of the sum of their power ratios.

\[L_{total} = 10 \log_{10} \sum_i 10^{L_i / 10} \tag{37}\]

Equation 38, Sink Rate from Power and Glide Ratio. Sink rate is power over weight, or equivalently speed over the lift-to-drag ratio. Schweizer SGS 2-32

\[V_{sink} = \frac{P}{W} = \frac{V}{L/D} \tag{38}\]

Equation 39, Bespoke Minimum Sink Rate of the X-26A. At the minimum-power point and the light weight, with the best-glide speed and lift-to-drag ratio that the assumed efficiency and zero-lift drag produced, the sink rate is about 129 feet per minute against a quoted 124.

\[V_{mp} = 0.760 \times 54.7 = 41.6 \, \text{mph} = 61.0 \, \text{ft/s}, \qquad V_{sink} = \frac{61.0}{(0.866)(32.7)} = 2.16 \, \text{ft/s} = 129 \, \text{ft/min} \tag{39}\]

Notation

$L$, the lift
$D$, the drag, and in Equations 34 and 35 the propeller diameter
$e$, the Oswald efficiency, taken as 0.90
$A$, the wing aspect ratio
$C_{D_0}$, the zero-lift drag coefficient, taken as 0.012
$C_L$, the lift coefficient, with $C_L^{\ast}$ its value at best glide
$b$, the wing span
$S$, the wing area
$W$, the weight
$\rho$, the air density
$V_{bg}$, the best-glide speed, with $V_{mp}$ the minimum-power speed
$p$, the roll rate, and in Equation 26 the sound pressure
$y$, the spanwise station
$C_{n_p}$, the yawing moment derivative due to roll rate
$C_{n_\beta}$, the directional stiffness derivative
$\beta$, the sideslip angle
$C_{l_{\delta_a}}$, the aileron roll power
$C_{l_p}$, the roll damping derivative
$pb/2V$, the helix angle of a steady roll
$\phi$, the bank angle
$C_{L_{max}}$, the maximum lift coefficient
$P$, the power required
$\text{SPL}$, the sound pressure level
$L_{amb}$, the ambient sound level
$r$, the slant range from source to listener
$N_b$, the number of propeller blades
$\alpha$, the atmospheric absorption coefficient
$V_{tip}$, the propeller tip speed
$J$, the advance ratio
$M_{tip}$, the tip Mach number

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Sechter, Brendan. 2025. “X-Planes: Convair X-12.” Brendan A R Sechter’s Development Blog, October 18. https://sgeos.github.io/aerospace/history/engineering/2025/10/18/x_planes_convair_x12.html
Sechter, Brendan. 2025. “X-Planes: Ryan X-13 Vertijet.” Brendan A R Sechter’s Development Blog, October 19. https://sgeos.github.io/aerospace/history/engineering/2025/10/19/x_planes_ryan_x13.html
Sechter, Brendan. 2025. “X-Planes: Bell X-14.” Brendan A R Sechter’s Development Blog, October 20. https://sgeos.github.io/aerospace/history/engineering/2025/10/20/x_planes_bell_x14.html
Sechter, Brendan. 2025. “X-Planes: North American X-15.” Brendan A R Sechter’s Development Blog, October 21. https://sgeos.github.io/aerospace/history/engineering/2025/10/21/x_planes_north_american_x15.html
Sechter, Brendan. 2025. “X-Planes: Bell X-16.” Brendan A R Sechter’s Development Blog, October 22. https://sgeos.github.io/aerospace/history/engineering/2025/10/22/x_planes_bell_x16.html
Sechter, Brendan. 2025. “X-Planes: Lockheed X-17.” Brendan A R Sechter’s Development Blog, October 23. https://sgeos.github.io/aerospace/history/engineering/2025/10/23/x_planes_lockheed_x17.html
Sechter, Brendan. 2025. “X-Planes: Hiller X-18.” Brendan A R Sechter’s Development Blog, October 24. https://sgeos.github.io/aerospace/history/engineering/2025/10/24/x_planes_hiller_x18.html
Sechter, Brendan. 2025. “X-Planes: Curtiss-Wright X-19.” Brendan A R Sechter’s Development Blog, October 25. https://sgeos.github.io/aerospace/history/engineering/2025/10/25/x_planes_curtiss_wright_x19.html
Sechter, Brendan. 2025. “X-Planes: Boeing X-20 Dyna-Soar.” Brendan A R Sechter’s Development Blog, October 26. https://sgeos.github.io/aerospace/history/engineering/2025/10/26/x_planes_boeing_x20.html
Sechter, Brendan. 2025. “X-Planes: Northrop X-21.” Brendan A R Sechter’s Development Blog, October 27. https://sgeos.github.io/aerospace/history/engineering/2025/10/27/x_planes_northrop_x21.html
Sechter, Brendan. 2025. “X-Planes: Bell X-22.” Brendan A R Sechter’s Development Blog, October 28. https://sgeos.github.io/aerospace/history/engineering/2025/10/28/x_planes_bell_x22.html
Sechter, Brendan. 2025. “X-Planes: Martin Marietta X-23 PRIME and a Contested Assignment.” Brendan A R Sechter’s Development Blog, October 29. https://sgeos.github.io/aerospace/history/engineering/2025/10/29/x_planes_martin_marietta_x23.html
Sechter, Brendan. 2025. “X-Planes: Martin Marietta X-24.” Brendan A R Sechter’s Development Blog, October 30. https://sgeos.github.io/aerospace/history/engineering/2025/10/30/x_planes_martin_marietta_x24.html
Sechter, Brendan. 2025. “X-Planes: Bensen X-25.” Brendan A R Sechter’s Development Blog, October 31. https://sgeos.github.io/aerospace/history/engineering/2025/10/31/x_planes_bensen_x25.html

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
X-Planes: Lockheed Martin X-35 2025-11-10
X-Planes: Orbital Sciences X-34 2025-11-09
X-Planes: Lockheed Martin X-33 2025-11-08
X-Planes: Boeing X-32 2025-11-07
X-Planes: Rockwell-MBB X-31 2025-11-06
X-Planes: Rockwell X-30 and the National Aero-Space Plane 2025-11-05
X-Planes: Grumman X-29 2025-11-04
X-Planes: Osprey X-28 Sea Skimmer 2025-11-03
X-Planes: Lockheed X-27 2025-11-02

The Research Question

Programme Origin

The Vehicles

Sizing From First Principles

The One Relation

Why This Aircraft Teaches Adverse Yaw

The Magnitude and the Rate

An Observability Index

How Slowly the Demonstration Could Be Flown

Dependent Systems

Reading the Same Relation as a Power Requirement

Best Glide and Minimum Power

What Quiet Means, Quantitatively

Why the Simple Model Is the Right One

The Propeller as the Lever

Why Quieting One Source Has a Ceiling

What It Gave Up to Carry an Engine

The Sensors and the Mission

The Flight Test Record

Comparison With Ground Prediction

What the Data Changed

The Contemporary Literature

The X-26A’s Argument Became a Regulation

Adverse Yaw, Identified From Data

Quiet Flight, Attempted Again

The Mission Went Unmanned and Solved the Acoustic Problem by Accident

And Now Everyone Wants to Hear the Aircraft

Propeller Noise, Computed

The Very Efficient Aeroplane

Training Transfer and Simulator Fidelity

What the Survey Shows

Propeller aerodynamics, design and propulsion

Propeller and rotor noise

Aircraft noise sources, measurement, prediction and reduction

Performance, power required, endurance and range

Aeroelasticity, flutter and gust loads

Flight test, system identification and parameter estimation

Pilot training, simulation, human factors and safety

Lateral control, ailerons and adverse yaw

Sailplanes, gliders and soaring

Outdoor sound propagation and atmospheric absorption

Flying and handling qualities

Lateral-directional stability, roll damping and coupling

Community noise, annoyance and psychoacoustics

Induced drag, span loading and the high aspect ratio wing

Acoustic and aural detection of aircraft

Unmanned aircraft design and operation

Engine exhaust noise and mufflers

Loss of control, upset recovery, stall and spin

Flight control, control allocation and fault tolerance

Aerodynamics, airfoils and aerodynamic design

Airframe noise, cabin noise and vibration

Surveillance, reconnaissance and observation

Electric, hybrid-electric and solar-powered aircraft

Flight dynamics, stability and simulation models

Other aeronautical literature

Wind tunnels, models and test technique

Rotorcraft and vertical lift flight mechanics

Where the Framing Breaks Down

The Source Base

The Definition of Primary

Thin Subjects

What the Survey Admits

Epistemic State

Out of Scope

Conclusion

Equations

Notation

References

Primary Sources, Peer-Reviewed

Primary Sources, Non-Peer-Reviewed

Secondary Sources

Commercial Sources

General Sources

Tertiary Sources

Related Posts

Related posts

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