X-Planes: Boeing X-48

On 20 July 2007 an aeroplane weighing about as much as three passengers took off from Rogers Dry Lake, and the number that matters about it is 240. [Risch et al 2009] The X-48B spans 20.4 feet. The aeroplane it was built to describe spans 240 feet, and every claim the programme made about that larger machine had to travel across a factor of 8.5 percent to get there [Regan 2008] [Boeing flies X-48C blended wing body research aircraft].

This is the forty-ninth article in the X-Planes series, following the X-1, the X-2, the X-3, the X-4, the X-5, the X-6, the X-7, the X-8, the X-9, the X-10, the X-11, the X-12, the X-13, the X-14, the X-15, the X-16, the X-17, the X-18, the X-19, the X-20, the X-21, the X-22, the X-23, the X-24, the X-25, the X-26, the X-27, the X-28, the X-29, the X-30, the X-31, the X-32, the X-33, the X-34, the X-35, the X-36, the X-37, the X-38, the X-39, the X-40, the X-41, the X-42, the X-43, the X-44, the X-45, the X-46, and the X-47.

One airframe flew 122 times over nearly six years, as two aeroplanes, and the record of those flights is extensive. The second X-48B flew 92 times and was then rebuilt as the X-48C, which flew 30 more [Second X-48B modified into X-48C configuration, NASA Dryden] [X-48 Research, All Good Things Must Come to an End, NASA]. It flew in two configurations, through envelope expansion, parameter identification, engine-out testing and deliberate approaches to the limit of controlled flight [X-48 Research, All Good Things Must Come to an End, NASA].

It is the first aeroplane in this series whose central question is about the instrument rather than the vehicle. The previous three articles were unmanned combat aircraft. This one is a transport configuration, and the interesting thing about it is not what it did but what its size permits anyone to conclude.

The Research Question

The blended wing body was never in doubt at cruise, and was entirely in doubt on approach. The configuration’s case is aerodynamic efficiency, and by the time the X-48 flew, the cruise argument had been made in analysis and in the tunnel [Liebeck 2004]. What no tunnel settles is whether a large tailless aeroplane with twenty trailing-edge surfaces and no horizontal tail can be flown safely at low speed by a line pilot, and where it stops being controllable.

A free-flight model answers that question, and it answers it by giving something up. A model cannot match every dimensionless group at once. Matching the ratio of inertial to gravitational force, which is the Froude number, makes the model move like the aeroplane. Matching the ratio of inertial to viscous force, which is the Reynolds number, makes the air behave around the model as it does around the aeroplane. At any scale below one, those two demands conflict, and the free-flight tradition resolves the conflict in favour of Froude [Chambers 2010].

This article asks what the X-48B’s scale factor bought and what it cost. The answer can be computed, and it bears directly on the most quoted result of the flight programme.

Programme Origin

Four scaled blended wing bodies preceded the answer, and two of them never flew. The designation record for the family is set out in the specialist directory [Parsch, Boeing X-48, Directory of U.S. Military Rockets and Missiles], and the general configuration has a literature of its own reaching back to the tailless transports of the 1940s [Wooldridge, Winged wonders, the story of the flying wings] [Blended wing body].

The first was the BWB-17, a 17-foot-span model weighing 120 pounds, built at Stanford University under the sponsorship of the National Aeronautics and Space Administration, abbreviated NASA, and flown on 29 July 1997 at El Mirage Dry Lake. It was dynamically scaled, carried an onboard computer for stability augmentation, and demonstrated good handling qualities within the normal envelope [Liebeck 2004].

The second was the X-48A. In 2000 NASA and Boeing began a 35-foot-span remotely piloted model, and the designation was allocated in late 2001 [Parsch, Boeing X-48, Directory of U.S. Military Rockets and Missiles]. It was described as a 14 percent scale vehicle of the 450-passenger study aircraft [X-48 Blended Wing Body, GlobalSecurity] [Parsch, Boeing X-48, Directory of U.S. Military Rockets and Missiles]. After about a year the programme was cancelled and NASA redirected its effort to a 12-foot-span free-flight model for the Langley Full-Scale Tunnel [Chambers 2010]. That redirection is the most consequential decision in this article, and the section on scaling prices it.

The third and fourth are the two X-48B airframes, of which only the second flew [Risch et al 2009]. Boeing Phantom Works took the lead on the X-48B in 2006 with NASA and the Air Force Research Laboratory [Boeing Phantom Works to lead research on X-48B blended wing body concept] [X-48 Blended Wing Body, GlobalSecurity]. Two X-48B airframes were built by Cranfield Aerospace in the United Kingdom to Boeing’s specifications [Cranfield Aerospace Solutions] [Boeing X-48]. Ship 1 went to the Langley Full-Scale Tunnel for 250 hours of testing in May 2006, and Ship 2 became the flight vehicle [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. Ship 2 was later rebuilt as the X-48C [Second X-48B modified into X-48C configuration, NASA Dryden].

Sizing From First Principles

The Geometry Closes Exactly

Two numbers are published separately and their ratio is not approximate. NASA’s fact sheet and the flight-test papers give the X-48B a span of 20.4 feet and call it an 8.5 percent scale vehicle [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Risch et al 2009], and Boeing gives the full-scale aeroplane a span of 240 feet [Boeing flies X-48C blended wing body research aircraft]. Taking the ratio,

\[n = \frac{20.4\ \text{ft}}{240\ \text{ft}} = 0.085000\]

which agrees with the published 8.5 percent to fourteen decimal places. The agreement establishes that the reference vehicle is a real design with a fixed span and that its span was no round number attached afterwards, and every relation below inherits that exactness.

What Froude Matching Does to Everything Else

Two dimensionless groups compete and only one can be held. The Froude number is the ratio of inertial to gravitational force and the Reynolds number is the ratio of inertial to viscous force,

\[Fr = \frac{V^{2}}{Lg}, \qquad Re = \frac{VL}{\nu}\]

Setting the model’s Froude number equal to the aeroplane’s fixes the speed ratio, and it does so without reference to the air at all,

\[\frac{V_m^{2}}{L_m g} = \frac{V_f^{2}}{L_f g} \implies r_V = \frac{V_m}{V_f} = \sqrt{\frac{L_m}{L_f}} = \sqrt{n}\]

The mass condition is a separate requirement, and it is usually forgotten. A dynamic model must also match the relative density factor, which compares the model’s mass to the air it displaces,

\[\sigma = \frac{m}{\rho l^{3}}\]

so that the weight ratio carries an atmospheric term,

\[r_W = \frac{n^{3}}{\sigma}\]

When the model and the aeroplane fly in the same air, $\sigma$ is one and the term disappears. The article returns to what happens when they do not.

Holding the Froude number and the relative density fixed determines every other ratio by dimensions alone. With $n$ the length ratio and the model flying in the same air as the aeroplane,

\[r_V = \sqrt{n}, \qquad r_t = \sqrt{n}, \qquad r_\omega = \frac{1}{\sqrt{n}}\] \[r_W = n^3, \qquad r_I = n^5, \qquad r_{Re} = n^{3/2}\]

The Reynolds ratio is not an independent choice but a consequence, being the product of the speed ratio already fixed by Froude and the length ratio,

\[r_{Re} = r_V \, r_L = n^{1/2} \cdot n = n^{3/2}\]

and that single line states the cost of the decision in full. Two further ratios follow the same way and both matter later. The dynamic pressure and the wing loading go as

\[r_q = \frac{\rho V_m^{2}}{\rho V_f^{2}} = r_V^{2} = n, \qquad r_{W/S} = \frac{n^{3}}{n^{2}} = n\]

The weight goes as the cube because it is a force and a force at matched Froude number scales as $\rho V^2 L^2$, which is $n \cdot n^2$. The underlying rigid-body equations are standard [Etkin and Reid, Dynamics of flight] [McCormick, Aerodynamics, aeronautics and flight mechanics]. The exponent of three halves in the Reynolds row comes from that product of the velocity and length ratios.

At $n = 0.085$ these evaluate to the following.

Quantity	Ratio	Value at 8.5 percent
Length	$n$	0.0850
Velocity	$n^{1/2}$	0.2915
Time	$n^{1/2}$	0.2915
Angular rate	$n^{-1/2}$	3.430
Weight and force	$n^{3}$	$6.141 \times 10^{-4}$
Moment of inertia	$n^{5}$	$4.437 \times 10^{-6}$
Reynolds number	$n^{3/2}$	0.02478
Thrust to weight	$1$	1.000

Two rows carry the argument. The model’s angular motions run 3.430 times faster than the aeroplane’s, and the model’s Reynolds number is 1/40.35 of the aeroplane’s.

The Pilot Does Not Scale

Time compression constrains the pilot as much as the aeroplane. Any interval scales as

\[t_m = t_f \sqrt{n} = 0.2915 \, t_f\]

so a motion that the full-scale aeroplane would develop over three seconds develops in the model in

\[t_m = 3 \times 0.2915 = 0.875\ \text{s}\]

and the angular rates that go with it are faster by the reciprocal,

\[r_\omega = \frac{1}{\sqrt{n}} = 3.430\]

The aeroplane is on a dry lake bed and the pilot is in a ground station, and the pilot’s reaction time is not multiplied by 0.2915 to match. [Risch et al 2009]

NASA’s account of dynamic model testing acknowledges the problem, noting that because a model’s angular motions are so much faster than the aeroplane’s, the models may be difficult to control, and that the response has often been to share the piloting task among more than one person [Chambers 2010].

This series has measured this before at a gentler scale. The X-36 was a 28 percent remotely piloted tailless demonstrator [X-36 Tailless Fighter Agility Research Aircraft, NASA], and the same relations give a time compression of 1.890 and a Reynolds penalty of 6.75. Against it,

\[\frac{r_t^{-1}(0.085)}{r_t^{-1}(0.28)} = 1.815, \qquad \frac{r_{Re}^{-1}(0.085)}{r_{Re}^{-1}(0.28)} = 5.979\]

The X-48B’s pilot faced dynamics 1.815 times faster than the X-36’s, and its aerodynamics were 5.979 times further from full scale. The X-36 article argued that a scale factor is a statement about what an experiment is able to measure. The X-48B repeats that argument at nearly twice the severity.

Reynolds Number in Absolute Terms and at Altitude

A ratio of 40.35 does not locate either aeroplane on the Reynolds scale, and the absolute values decide whether the mismatch matters. Using a reference chord and the published maximum speed of 118 knots [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Vicroy 2011],

\[Re = \frac{V c}{\nu}, \qquad c = \frac{S}{b} = \frac{100.5}{20.4} = 4.926\ \text{ft}\]

The programme’s correlation update supplies the wing area of 100.5 square feet [Vicroy 2011]. The ratio below does not depend on it, because the chord cancels.

At sea level, with $\nu_0 = 1.5723 \times 10^{-4}\ \text{ft}^2/\text{s}$,

\[Re_{\text{model}} = \frac{199.2 \times 4.926}{1.5723 \times 10^{-4}} = 6.24 \times 10^{6}\]

and the corresponding full-scale condition, at $V_f = V_m/\sqrt{n}$ and $c_f = c/n$,

\[Re_{\text{full}} = \frac{683.1 \times 58.0}{1.5723 \times 10^{-4}} = 2.52 \times 10^{8}\]

Both are above the range where a boundary layer is deciding whether to be turbulent at all, and they are two orders of magnitude apart.

The published speed also checks the scaling. Inverting the speed ratio on the model’s maximum,

\[V_f = \frac{118}{\sqrt{0.085}} = 404.7\ \text{kt}\]

a sensible cruise speed for a large subsonic transport, and a second piece of evidence for a real reference design.

The atmosphere then makes the mismatch worse, and nowhere else in this article does the standard atmosphere earn its keep. The model flew to a ceiling of 10,000 feet [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Vicroy 2011], inside a working area that reached from the ground to 10,000 feet above mean sea level [Risch et al 2009], while the full-scale aeroplane’s low-speed regime is near the ground. Kinematic viscosity rises with altitude,

\[\nu(h) = \frac{\mu(h)}{\rho(h)}, \qquad \frac{\nu(10{,}000)}{\nu(0)} = \frac{2.0135 \times 10^{-4}}{1.5723 \times 10^{-4}} = 1.281\]

so a model tested at its ceiling against an aeroplane approaching at sea level suffers

\[P_{\text{effective}} = n^{-3/2} \times \frac{\nu(10{,}000)}{\nu(0)} = 40.35 \times 1.281 = 51.7\]

The effective penalty therefore lies between 40.35 and 51.7, depending on the test altitude, and the larger figure applies to any manoeuvre flown high.

What Cancelling the X-48A Cost

The penalty is a function of span alone once the reference is fixed, since $n = b/b_{\text{ref}}$ gives

\[P(b) = \left(\frac{b_{\text{ref}}}{b}\right)^{3/2}, \qquad \tau(b) = \left(\frac{b_{\text{ref}}}{b}\right)^{1/2}\]

Evaluated against the X-48B’s 240-foot reference, the three spans NASA planned or flew price out as follows. The 12-foot model is the 5 percent free-flight model of the Langley Full-Scale Tunnel [Vicroy 2011].

Vehicle	Span	Scale	Time compression	Reynolds penalty
X-48A, planned and cancelled	35 ft	0.1458	2.619	17.96
X-48B, flown	20.4 ft	0.0850	3.430	40.35
Langley free-flight model	12 ft	0.0500	4.472	89.44

The cost of the substitution is a ratio of two such penalties and needs no other quantity,

\[\frac{P(20.4)}{P(35)} = \left(\frac{35}{20.4}\right)^{3/2} = 2.247, \qquad \frac{\tau(20.4)}{\tau(35)} = \left(\frac{35}{20.4}\right)^{1/2} = 1.310\]

Cancelling the 35-foot aeroplane and flying the 20.4-foot one multiplied the Reynolds shortfall by 2.247 and made the aeroplane 31 percent quicker in its own time. Those two factors price the 2002 decision in the only units that can express it. The table holds the reference fixed, because the substitution posed that comparison. The X-48A itself was described as a 14 percent vehicle of the 450-passenger study aircraft, which implies a reference span of 250 feet, close to the 249 feet of the BWB-450 baseline, and against that reference its own time compression is 2.673 and its own Reynolds penalty 19.09 [X-48 Blended Wing Body, GlobalSecurity] [Liebeck 2004]. It is not an argument that the decision was wrong, since a 35-foot vehicle is a different programme in cost, airspace and risk, but it is the quantity the decision traded.

The Vehicle Implied by the Model’s Weight

A dynamically scaled model is weight-scaled, so the relation can be run backwards. Taking the maximum weight of 525 pounds given in the flight-test papers [Risch et al 2009] [Regan 2008] and inverting the cube,

\[W_{\text{full}} = \frac{525\ \text{lb}}{n^3} = 8.549 \times 10^{5}\ \text{lb}\]

That figure assumes $\sigma = 1$, the term the earlier section set aside. Restoring it,

\[W_{\text{full}} = \frac{W_m}{n^{3}} \cdot \frac{\rho_f}{\rho_m}\]

and evaluating for three readings of where the model’s condition sits,

Model condition	$\rho_m/\rho_0$	Implied full-scale weight
same air as the aeroplane	1.0000	854,875 lb
Rogers Dry Lake, 2,300 ft	0.9344	914,885 lb
ceiling, 10,000 ft	0.7385	1,157,634 lb

The field reading takes the lake bed at about 2,300 feet [Rogers Dry Lake]. The figure of 854,875 pounds can serve only as a lower bound, and the article uses it as one.

No technical source consulted states the reference vehicle’s weight, so the figure is a derivation. A magazine account published before the first flight calls the X-48B a scaled-down model of a theoretical 500-ton, 240-foot-wide aircraft [Jacobs 2007, Thinking outside the tube, Wired]. Read as 1,000,000 pounds, that round figure lies inside the range above, and the three readings come to 0.855, 0.915 and 1.158 of it. The derivation can also be tested against a published design. Among the sources consulted, the only blended wing body design with both a published weight and a published span is Liebeck’s second-generation airliner, sized for 800 passengers, with a maximum takeoff gross weight of 823,000 pounds on a span of 280 feet [Liebeck 2004]. Scaling that design geometrically to a 240-foot span,

\[W(240) = 823{,}000 \times \left(\frac{240}{280}\right)^{3} = 518{,}274\ \text{lb}\]

gives a comparison of

\[\frac{W_{\text{full}}}{W(240)} = \frac{854{,}875}{518{,}274} = 1.649\]

Geometric scaling holds the shape and lets the wing loading grow with span. Holding the wing loading instead makes weight follow the square of span,

\[W_{2}(240) = 823{,}000 \times \left(\frac{240}{280}\right)^{2} = 604{,}653\ \text{lb}\]

and the two laws differ by the factor 280/240, or 1.167. Against each,

Model condition	Over the cube law	Over the square law
same air as the aeroplane	1.649	1.414
Rogers Dry Lake, 2,300 ft	1.765	1.513
ceiling, 10,000 ft	2.234	1.915

so the vehicle implied by the model’s weight is between 1.414 and 1.649 times as heavy as the passenger design brought to the same span, and between 1.513 and 1.765 times as heavy on the field-elevation reading. The choice of scaling law changes the size of the excess by a sixth, and no reading brings the ratio near one.

The excess is large, and the programme’s description of the full-scale aeroplane accounts for its direction. Boeing describes the 240-foot aeroplane as a heavy-lift, subsonic airplane for military applications such as aerial refuelling and cargo missions [Boeing flies X-48C blended wing body research aircraft], and the Air Force’s stated interest was a multi-role, long-range, high-capacity military transport [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. A freighter is denser than an airliner of the same dimensions, as the conventional airlifter it would replace shows [Boeing C-17 Globemaster III], and the weight relations behind that comparison are the standard conceptual-design ones [Raymer, Aircraft design, a conceptual approach] [Torenbeek, Synthesis of subsonic airplane design] [Nicolai and Carichner, Fundamentals of aircraft and airship design]. The model’s weight therefore agrees with the heavy military vehicle the programme described and does not agree with a passenger design of the same span. The scale relations fix the size of that excess. They do not show how much of it payload density explains, and this article does not attempt that division.

Thrust Is Invariant Under Froude Scaling and This Model Does Not Match It

Thrust is a force, so it scales as $n^3$, and thrust to weight is therefore the same number for the model and the aeroplane. That makes it directly checkable, with the installed thrust of 54 pounds an engine from the flight-test papers [Risch et al 2009] [Regan 2008] and the full-scale thrust from Liebeck’s design [Liebeck 2004].

\[\left(\frac{T}{W}\right)_{\text{model}} = \frac{3 \times 54\ \text{lbf}}{525\ \text{lb}} = 0.3086\] \[\left(\frac{T}{W}\right)_{\text{full}} = \frac{3 \times 61{,}600\ \text{lbf}}{823{,}000\ \text{lb}} = 0.2245\] \[\frac{(T/W)_{\text{model}}}{(T/W)_{\text{full}}} = \frac{0.3086}{0.2245} = 1.374\]

The model carries 1.374 times the thrust to weight of the aeroplane it represents. Such a margin is no defect. A model that must take off from a lake bed, climb to a test altitude inside a small working area and go around from an approach needs margin the transport does not.

But it means the demonstration is tilted, and the direction is computable. Thrust to weight is one of the handful of ratios that fixes an aeroplane’s performance at all [Anderson, Aircraft performance and design].

The quantity that matters for engine-out is the asymmetric thrust carried as a fraction of weight, which for $N_e$ equal engines with one failed is

\[\frac{\Delta T}{W} = \frac{T}{W} \cdot \frac{1}{N_e}\]

Evaluating for the two models and for the full-scale trijet,

\[\left(\frac{\Delta T}{W}\right)_{B} = \frac{0.3086}{3} = 0.10286, \qquad \left(\frac{\Delta T}{W}\right)_{C} = \frac{0.3560}{2} = 0.17800\] \[\left(\frac{\Delta T}{W}\right)_{\text{full}} = \frac{0.2245}{3} = 0.07485\]

against which the two aeroplanes stand at

\[\frac{0.10286}{0.07485} = 1.374, \qquad \frac{0.17800}{0.07485} = 2.378, \qquad \frac{0.17800}{0.10286} = 1.731\]

An engine-out yaw moment is a thrust asymmetry, so a model with 37 percent more thrust to weight produces a proportionally larger upset than the full-scale aeroplane would at the same flight condition. Engine-out control was a stated flight-test objective, specified at low speed, in the takeoff configuration and at minimum operating empty weight with an outboard engine failed [Risch et al 2009]. In the first 39 flights it was evaluated at a benign condition, each engine in turn reduced to idle, and found satisfactory [Risch et al 2009]. So the specified test is harder than the aeroplane will face, and a pass is conservative. The X-48C’s engine-out case is harder still, at 2.378 times the full-scale upset, because losing one engine of two removes half the thrust where losing one of three removes a third, and the C model’s thrust to weight is higher as well. This tilt errs on the comfortable side, the opposite of the tilt found in X-Planes: Lockheed Martin X-35.

The Two Aircraft

	X-48B	X-48C
First flight	20 July 2007	7 August 2012
Last flight	2010	9 April 2013
Flights	92	30
Span	20.4 ft	just over 20 ft
Gross weight	523 to 525 lb	about 500 lb
Engines	3 turbojets, 54 lbf installed each	2 turbojets, 89 lbf each, planned at 75
Thrust to weight	0.309	0.356
Vertical surfaces	winglets with rudders at the tips	twin tails moved inboard
Aft body	as designed	extended about 2 ft
Maximum speed	118 kt	about 140 mph
Ceiling	10,000 ft	10,000 ft
Endurance	30 to 40 min, 13 gal fuel	about 30 min

The figures in the table are from the fact sheet, the flight-test papers, the correlation update and the programme’s announcements [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Risch et al 2009] [Regan 2008] [Vicroy 2011] [X-48 Research, All Good Things Must Come to an End, NASA] [Boeing flies X-48C blended wing body research aircraft] [X-48 Blended Wing Body, GlobalSecurity]. The sources disagree about the C model’s engines and the disagreement is load-bearing. NASA’s fact sheet gives two engines of 89 pounds thrust, while the programme’s 2011 presentation gives two of 75 as planned [Vicroy 2011] [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. The later figure is more likely to describe what was fitted and the earlier to describe what was planned, and this article uses 89 while reporting both, because the engine-out arithmetic of the scaling section above depends on which is right. At 75 pounds the thrust to weight falls from 0.356 to 0.300 and the engine-out factor from 2.378 to 2.004, which moves the size of the conclusion and not its direction.

The C model was a noise aeroplane and its modifications were acoustic in intent. The winglets were relocated inboard next to the engine exhaust ducts, becoming twin vertical tails, and the aft deck was extended about two feet rearward, both to shield engine noise from the ground [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Boeing flies X-48C blended wing body research aircraft]. The low-noise configuration descends from NASA’s Environmentally Responsible Aviation studies of aircraft two decades ahead [The Environmentally Responsible Aviation project, a technology development project].

Two of those changes work against the axis the programme had already named as weakest. Moving a vertical surface inboard on a swept planform moves it forward, shortening its moment arm about the centre of gravity, and the aft-deck extension recovers part of that arm rather than adding to it. Separately, the C model has two engines where the B model had three. NASA reports that the handling qualities of the C model differed from the B model and that new flight control limiters were written for it, the clearest published statement that the noise modification was not free [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090].

The X-48C Made the Weak Axis Weaker

The programme’s own stated hypothesis was that yaw control is poor throughout the flight envelope [Risch et al 2009]. The noise modification then acted on that axis twice, in the same direction, and neither action was intended to. [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]

The first is the engine count. The asymmetric thrust fraction computed above rises from 0.10286 to 0.17800, a factor of 1.731 against the B model.

The second is the moment arm. Directional authority from a vertical surface scales with the tail volume coefficient,

\[V_v = \frac{S_v \, l_v}{S \, b}\]

in which $l_v$ is the distance from the centre of gravity to the surface’s aerodynamic centre. On a swept planform, moving a surface inboard moves it forward, because the structure it attaches to sweeps aft with span,

\[\Delta l_v = \Delta y \, \tan \Lambda\]

The sweep angle of the X-48’s outer trailing edge is not published in any source consulted, so the shift appears here only as a sensitivity. Taking the winglets from the tip at $y = 10.2$ ft to a station near the exhaust ducts at roughly 2.5 ft, so $\Delta y = 7.7$ ft,

Assumed sweep	Forward shift	Net after the 2 ft aft-deck extension
30 degrees	4.45 ft	2.45 ft
35 degrees	5.39 ft	3.39 ft
40 degrees	6.46 ft	4.46 ft

The aft deck was extended about two feet rearward, which acts in the recovering direction [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. Against a tail arm of order ten feet on a twenty-foot aeroplane, a net loss of two to four feet is a reduction in $V_v$ of roughly a quarter to nearly a half, before any account is taken of the change in surface area or of the interference between a tail and an exhaust plume.

Both effects push the same way on the axis already named as weakest, and NASA records the consequence. The project team wrote flight control system modifications for the C model, including limiters to keep it inside a safe envelope, because its handling qualities differed from the B model’s [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. The arithmetic above is one reading of why.

Dependent Systems

Control Allocation Across Twenty Surfaces

The X-48B carries twenty individually actuated control surfaces along the trailing edge of the wing and the winglets, and those twenty provide all of its control power [Risch et al 2009]. There is no horizontal tail, and the rudders sit on the winglets at the tips [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090]. Pitch, roll and yaw are produced by blending surfaces that each contribute to more than one axis, and the outboard elevons split into drag rudders for yaw in the manner of the B-2 [Liebeck 2004] [Northrop Grumman B-2 Spirit].

The test plan listed an assessment of the dynamic interaction of all twenty surfaces among its objectives [Risch et al 2009], an unusual thing to have to schedule and a direct consequence of the configuration.

The Leading Edge, Flown Both Ways

Leading-edge slats were fitted to increase maximum lift for takeoff and landing, and the flight programme tested two leading-edge configurations, slats extended and slats retracted, bolted in place before each flight and interchangeable between flights [Risch et al 2009] [Regan 2008]. By bracketing the leading edge, the programme hedged where the scaling is weakest, whether or not it was framed that way at the time.

The Ground Station

The aeroplane was flown from a ground control station using conventional stick, rudder and throttle, inside an irregular working area on the north side of Edwards Air Force Base whose longest straight dimension is about 5.5 nautical miles [Risch et al 2009]. An aeroplane whose motions run 3.430 times fast, inside 5.5 nautical miles, is a demanding piloting task before any aerodynamics are considered.

The Flight Test Record

The programme flew 122 times, 92 as the X-48B and 30 as the X-48C [X-48 Research, All Good Things Must Come to an End, NASA]. The first 39 flights, from July 2007 to December 2008, which the progress paper describes as the first two phases of a planned three-phase programme, are documented in detail and are the basis for what follows [Risch et al 2009].

Testing proceeded in blocks. Envelope expansion came first, then parameter identification, stalls and engine-out work. Three weight configurations were flown, with empty weights of about 395, 405 and 430 pounds, and three centre-of-gravity positions separated by four inches of mean aerodynamic chord. Typical flights lasted 30 to 35 minutes and were limited by a 13-gallon fuel capacity [Risch et al 2009]. By the end of August 2009 the aeroplane had flown 58 flights, and the initial envelope expansion had reached 23 degrees angle of attack and 20 degrees of sideslip [Taylor 2009].

The approach to the limit of controlled flight was made in one-degree increments of angle of attack, descending at idle thrust, which the team judged the lowest-risk condition for probing uncontrollable flight. At each increment the pilot evaluated controllability in all three axes and performed a pitch-over recovery [Risch et al 2009].

The flight programme did not stop at 39 flights and the fuller picture is better. The correlation update calls the six-block campaign to flight 80 its Phase I, the same six blocks the progress paper had divided into three phases, alternating slats extended and slats retracted and ending in departure limiter assaults [Risch et al 2009]. Its summary of the phase reports the aeroplane as extremely manoeuvrable in roll, closely matching simulation for up-and-away flight and landing, and the flight control design as very robust [Vicroy 2011].

The stall results carry angles, and the difference between the two leading-edge configurations is large.

\[\alpha_{\text{stall}}^{\text{slats out}} = 24^\circ, \qquad \alpha_{\text{stall}}^{\text{slats in}} = 14^\circ, \qquad \Delta\alpha = 10^\circ\]

Slats extended, the aeroplane stalled successfully to 24 degrees and remained controllable three degrees beyond the angle of maximum lift. Slats retracted, it reached 14 degrees [Vicroy 2011]. Ten degrees is not a refinement. It gives the clearest available measure of how much the leading edge governs this configuration’s behaviour, which matters because the leading edge is where the Reynolds sensitivity lives.

The departure limiter assaults were, in the programme’s own words, highly successful [Vicroy 2011].

What they found earlier is still the article’s most quoted fact. Just below the predicted stall angle of attack the aeroplane became difficult to hold steady because of a sustained pitch bobble. At a limiting angle of attack the bobble subsided and the aeroplane departed in uncommanded wing roll-offs. The limiting angle was reached six times across three flights with three separate pilots in the slats-extended configuration, and twice with slats retracted. Every pitch-over recovery succeeded. One pilot described holding the aeroplane near the limit as attempting to balance it on the head of a pin [Risch et al 2009].

One detail matters more than the rest. When a pilot attempted to counter the roll-off with lateral stick, the input slightly delayed the roll-off and then produced a more abrupt wing drop [Risch et al 2009].

Comparison With Ground Prediction

The flight programme was flown against a body of prediction, and the record shows where the two met and where they did not. Before flight there were the design paper’s account of how the configuration should stall, the simulation, and a ground-test campaign of free-flight, rotary, forced-oscillation and high-Reynolds tunnel tests. Where the comparison closed, the programme says so. Its phase summary reports the aeroplane closely matching simulation for up-and-away flight and landing [Vicroy 2011], and the sustained pitch bobble appeared just below the predicted stall angle of attack [Risch et al 2009], both as set out in the flight test record above. The subsections below take the design intent for the stall, the instrument that answered the Reynolds question, and the comparisons that were poor or never made.

The Flight Result and the Design Intent Disagree

Liebeck’s published account of the configuration states that separation is initiated in the kink region between the outboard wing and the centrebody, that the outer wing flow remains attached and provides lateral control into the stall regime, and that this is the ideal spanwise location for the stall to begin because the ailerons remain effective and pitch-up is avoided [Liebeck 2004].

The X-48B found uncommanded wing roll-off, and found that lateral control made it worse. [Risch et al 2009] Those two statements are not compatible. The design intent is that the outboard wing keeps flying and the pilot keeps roll authority [Liebeck 2004]. The flight result is that the aeroplane rolls off uncommanded and that using roll authority sharpens the departure.

The Scale Factor Permits That Disagreement and Cannot Settle It

Separation onset and its spanwise progression are Reynolds-dependent phenomena. At a Reynolds number 1/40.35 of the full-scale value, the model’s separation may begin at a different station on the span and at a different angle of attack than the aeroplane’s. The disagreement between design intent and flight observation is therefore of the kind the scale factor permits, and further flying of the model cannot resolve it.

The limitation applies to the flight vehicle and not to the programme, and the rest of this section turns on that distinction.

The Programme Answered the Reynolds Question With a Different Instrument

The flight vehicle was never asked to carry the Reynolds-governed half alone.

The correlation update plots the ground-test campaign on axes of vehicle scale against chord Reynolds number, and the tests spread across it below the full-scale region of interest that the plot marks [Vicroy 2011]. Free-flight, forced-oscillation, rotary, large-angle and free spin and tumble tests sit at small scale and low Reynolds number. Static aerodynamic tests, the Arnold Engineering Development Center 16T tunnel and the National Transonic Facility sit at higher Reynolds numbers, the last reaching about 70 million against a region of interest that begins above about 90 million [Vicroy 2011]. The X-48B flight test occupies one point on that plane.

Dynamic fidelity and Reynolds number came from different instruments, and the programme ran both. A pressurised cryogenic tunnel buys Reynolds number and cannot fly. A free-flight model flies and cannot reach that Reynolds number. Neither substitutes for the other, and the correlation exercise joins them.

The verdict recorded on the free-flight method is favourable. The update reports that the free-flight test method provided good correlation with the observed one-g flight test limits [Vicroy 2011]. A subscale free-flight model, judged against the larger flight vehicle of the same configuration, predicted the limits well, a narrower and better-supported claim than the one usually made for the X-48, and one the record contains.

The Poor Comparison Was Somewhere Else Entirely

Asked where the ground-to-flight comparisons were poor, the programme does not name the stall. It names the pitching moment, with a cause unrelated to scaling, and an engine model that early analysis showed needed improving [Vicroy 2011].

The magnitude of the support interference effect on pitching moment was much larger than anticipated [Vicroy 2011]. The same configuration measured on a three-inch post with a pitch link and on a 1.2-inch bent sting in the Langley 14 by 22 foot tunnel gave materially different pitching-moment curves. The defect lies in how the model was held, not in how it was scaled, and on a tailless aeroplane trimmed by its own trailing edge the pitching moment is the quantity least able to absorb an error.

A second lesson is administrative, and the programme states it without qualification. Ground-to-flight correlation is difficult without a central repository of wind tunnel, flight, computational and simulation data [Vicroy 2011]. The finding concerns data management rather than aerodynamics, and only a programme running seven kinds of test on one configuration is in a position to reach a conclusion of that kind.

The programme also names what it could not compare. Transonic behaviour, held only in the National Transonic Facility and 16T data, and post-departure modes such as the falling leaf, the spin and the tumble, held only in large-angle, rotary and free spin and tumble data. Neither has a flight comparison at all [Vicroy 2011], and that absence is the precise form of the concern this article raises.

What the Data Changed

The comparisons changed the reading of the result and left the result itself alone. The flights and their recoveries stand as reported. What moves is how far each finding can be carried from a 20.4-foot aeroplane to a 240-foot one, and the dimensionless group that governs each finding settles it, as the scaling derivation established.

What Transfers and What Does Not

The division is clean and it follows from which group is matched.

Froude-governed and transferable. The character of the departure as a motion, the number of cycles it takes to develop, whether a pitch-over recovery works, the control law’s ability to hold the aeroplane, and the handling qualities of the whole low-speed envelope. These are dynamics, and the model was built to reproduce dynamics. The programme’s claim to have proved low-speed controllability throughout the envelope rests here and is sound [X-48 Research, All Good Things Must Come to an End, NASA].

Reynolds-governed and not transferable without further argument. The angle of attack at which the roll-off begins, the spanwise station at which separation starts, the maximum lift coefficient, and whether the slat is required. These are the properties of a boundary layer [Schlichting and Gersten, Boundary layer theory], and a model at 1/40.35 of the aeroplane’s Reynolds number is not evidence about them. That maximum lift rises with Reynolds number over this range is a standard result [Hoerner and Borst, Fluid-dynamic lift].

The objective list asks for both. One objective is to determine, via flight manoeuvres and dynamic-scaling relationships, the full-scale low-speed flight characteristics and departure onset boundaries [Risch et al 2009]. The first transfers from the flight vehicle alone and the second does not, and the scale factor’s entire content lies in the difference between them.

The programme did not confuse the two and its test campaign is the evidence. The criticism that survives is narrower and is about repetition rather than about method. The flight vehicle alone is easily read as having proved the configuration’s low-speed behaviour, when what it proved is the dynamic half, and the Reynolds half was pursued separately in higher-Reynolds tunnels that approached the full-scale value without reaching it [Vicroy 2011]. A short account of the X-48 tends to lose that distinction, and the distinction decides what the result means.

What the X-48 Validated

The X-48 validated a control system and a recovery technique for a configuration, on an aeroplane whose departure boundary is its own rather than the full-scale vehicle’s. The flight vehicle is usually credited with more, but this smaller claim is the more defensible one, and the programme as a whole claims more than the flight vehicle does, correctly, because it ran the tunnels that the aeroplane could not be.

What remained unknown in 2000 was whether a control system could keep a large tailless transport inside its envelope and recover it from the edge. The flight vehicle answered that, and answered it at a scale where the recovery had to run three and a half times quicker than on the aeroplane. The result is durable and does not need the departure boundary to be true.

The Contemporary Literature

Cluster	Records
Aerodynamics of the configuration	1,174
Blended and hybrid wing body configurations	636
Stall, departure and the uncommanded roll-off	541
Reynolds number, scale effect and the transfer to full scale	523
Flight control law design and envelope protection	500
Aircraft noise, shielding and the quiet configuration	462
Tailless stability and control, and directional authority	397
Transport aircraft design, sizing and fuel efficiency	314
Parameter identification and flight test technique	309
Propulsion, airframe integration and installed performance	288
High-lift devices, slats and separation control	213
Remotely piloted operation and the ground station	207
Control allocation and redundant control effectors	193
Dynamic scaling, similitude and what a subscale model can answer	189
Structures, materials and the airframe	174
Rotorcraft, V/STOL and powered lift	86
Aeroelasticity, flutter and flight vibration	82
Flight test instrumentation, air data and test data processing	69
Flight test programmes, organisations and their history	61
The atmosphere and the flight condition	60
Flight mechanics and aircraft performance	57
Unconventional wings, joined, oblique, swept forward, morphing and flexible	44
Flight simulation and simulators	43
Total	6,622

Aerodynamics of the configuration

The flow the vehicle lives in. Lift, drag, vortex behaviour, boundary layers, computation, wind tunnel technique and the effect of ice on the wing. The X-48’s aerodynamic question is a low-speed one, which is unusual in this series, because the cruise case was never in doubt and the approach and the stall were.

1,174 records. 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2004] [Lijewski 1978] [Lin and Wang 1993] [Lin et al 1997] [Lindqvist et al 2001] [Liu 2022] [Liu et al 2009] [Liu et al 2016] [Livingston 1965] [Lizak 1960] [Lo 1970] [Lo 1972] [Lo 1988] [Lo and Glassman 1975] [Lo and Oliver 1970] [Lo and Ulbrich 1991] [Lock 1963] [Lockheed-California Co Burbank 1964] [Lombardi 1995] [Lombardi and Morelli 1994] [Lombardi et al 1996] [Lombardi et al 1997] [Lorber et al 2018] [Lori et al 2007] [Losada Costoso et al 2024] [Lovell 1999] [Lowry et al 2001] [Loya et al 2020] [Luce 1949] [Luchuk et al 1982] [Luckring 1979] [Luckring 2004] [Luckring 2015] [Lund 2000] [Lupo et al 1998] [Lv et al 2022] [Ma et al 2015] [Ma et al 2016] [MacCormack 2007] [Macha and Buffington 1989] [Mack 1952] [Mack et al 2009] [Mack 1999] [MacMaster 2016] [Macwilkinson et al 1974] [Madsen et al 2003] [Maeder and Hall 1955] [Magness et al 1989] [Makino et al 2003] [Malfa et al 1991] [Malmuth 1984] [Malmuth and Cole 1984] [Malone and Sankar 1985] [Maniet 2001] [Manor and Wentz 1985] [Manuilovich 2021] [Marcum 2000] [Mark and Dehart 1976] [Martin 2008] [Martin et al 1976] [Martin et al 2008] [Martin et al 1993] [Martinz et al 1997] [Maryland Univ College Park 1962] [Maseland et al 2006] [Maslov et al 2008] [Matalanis et al 2011] [Mateescu 1986] [Matheny and Panageas 1981] [Matheson 1987] [Maxworthy and Cheng 1989] [May and Vatistas 2006] [McClinton et al 1998] [McCormick 1956] [McDowell and Williamson 1982] [McInville and Moore 1994] [McNally and Bach 1988] [Measurements of Discrete Vortex 1976] [Medved and Elfstrom 1986] [Merz 1968] [Methel et al 2022] [Methods for Drag Determination 2003] [Metkowski and Maughmer 2021] [Meznarsic 1986] [Meznarsic and Gross 1980] [Mialon et al 2010] [Mickle et al 2012] [Mignosi et al 1986] [Mikhail and Rainbird 1978] [Miles 1948] [Miller 1976] [Miller 1992] [Miller and Wood 1983] [Miller et al 2022] [Moellmann and O’Connor 1967] [Mohamed et al 2021] [Mokry 1972] [Mokry 1989] [Mokry 2001] [Mokry and Khalid 2000] [Molyneux 1972] [Moore and Frei 1983] [Moore and Inville 1995] [Moore et al 1993] [Morelli and Klein 1995] [Morelli and DeLoach 2003] [Morgan and Caster 1965] [Mori et al 2024] [Morino et al 1989] [Morphing WING REAL TIME 2010] [Morse 1956] [Mort et al 1986] [Moul and Taylor 1980] [Murali et al 2024] [Murawski 1999] [Murillo and McMasters 1983] [Murman 1979] [Murman 1982] [Murphy and Klein 2003] [Murphy and Schmidt 1953] [Murphy et al 2004] [Murphy et al 2016] [Murphy and Klein 2011] [Murri et al 1984] [Murthy and Wedemeyer 1990] [Myatt and Blake 1999] [Nafroni et al 2023] [Nagel and Thomas 1965] [Nakamura et al 1993] [Nambu et al 2012] [Nangia et al 2003] [NASA wake vortex research 1993] [Nastase 2008] [Naval Ordnance Systems Command Washington Dc 1957] [Nazeer et al 2021] [Neal 1970] [Nelson 1974] [Nesterov 1963] [Neville and Stephens 1993] [Newman et al 1982] [Newman et al 2014] [Nguyen and Urnes 2012] [Ni et al 2024] [Nicolaides 1952] [Nicolaides 1971] [Nicolaides et al 1967] [Nicolosi et al 2015] [Niedling 1980] [Nietubicz 1975] [Nikolic 2005] [Nixon and Farshchi 1987] [Noise Radiation from Turbulent 1976] [Nonweiler 1955] [Norris et al 1989] [Null and Shkarayev 2005] [Nyberg and Sorensen 1980] [O’Donnell and Mohseni 2018] [Obara and Lamar 2009] [Obayashi et al 1993] [Obayashi et al 1995] [Ocokoljić et al 2017] [Olejnik et al 2021] [Olsen 1965] [Olsen 1966] [Olwi and Ghazi 1991] [Ongarato 1968] [Orlik-Ruckemann 1983] [Oruganti and Narsipur 2020] [Othman and Kanazaki 2015] [Oudheusden et al 2004] [Ozger 2007] [Paglino and Beno 1971] [Pagliuca and Timme 2016] [Palko and Crawford 1982] [Palko and Lohr 1978] [Pallister et al 1992] [Pamadi et al 2000] [Panagiotou et al 2015] [Pandya and Aftosmis 2001] [Pankhurst 1958] [Park and Rokhsaz 2003] [Park et al 2021] [Parkinson 1986] [Pate 1980] [Patil and Navrátil 2024] [Patterson 1967] [Paul] [Payne and Henry E. 1961] [Peake] [Peigin and Epstein 2007] [Peitzman 1978] [Peng et al 2024] [Perkins et al 1977] [Pershing 1986] [Persoon et al 1980] [Pesch and Hess 2019] [Petoshin and Chasovnikov 2011] [Petrov 1993] [Pettit et al 1994] [Petty 1975] [Pfaff 1965] [Pfeiffer and King 2012] [Pfnür and Breitsamter 2019] [Phillips and Waggoner 1988] [Phillips et al 1970] [Phythian 1966] [Piat and Estève 2002] [Pindzola and Chew 1960] [Pindzola and Lo 1969] [Pindzola and Mozer 1956] [Platou 1968] [Polhamus 1983] [Poll 1986] [Poole and Cromack 1970] [Popov et al 2009] [Potapczuk and Bidwell 1990] [Pounds 1972] [Pounds and Walker 1980] [Prasannakumar et al 2024] [Presas et al 2024] [Prizirembel and Wen 1978] [Putman et al 1977] [Qin 2012] [Quanwei and Qiongkang 1989] [Quast et al 1990] [Quick 1937] [Quitter et al 2021] [Radespiel 1989] [Rae 1967] [Rae and Shojiro 1977] [Rahmani et al 2022] [Rakshith et al 2015] [Rambacher and Bons 2023] [Rambacher et al 2024] [Rao et al 2023] [Rasuo 2000] [Rathert et al 1949] [Ratvasky et al 2003] [Razgonyaev and Mason 1995] [Redd et al 1979] [Reed and Saric 2001] [Reichenbach et al 2011] [Reimer et al] [Reubush 1978] [Reubush 1979] [Revell et al 1975] [Reynolds 1963] [Reynolds 1995] [Rich 1973] [Richardson 1976] [Rife et al 1992] [Rill and Ganzer 1988] [Rinehart 1970] [Ringenbach 1989] [Rinoie et al 2004] [Risse et al 2014] [Rist 1994] [Rittenhouse 1959] [Rizk and Lovell 1986] [Rizk et al 1988] [Robins and Delisi 1989] [Rock et al 1999] [Rodgers 1963] [Roger et al 2023] [Rogers 1966] [Rogers 2013] [Rom 1992] [Rooney et al 1977] [Rose et al 1982] [Roskam et al 1980] [Ross et al 1987] [Rossow 2001] [Rowley 2008] [Roy and Mukherjee 2020] [Rubio and Ballard 1967] [Rudenko and Ryzhkova 1968] [Rueger and Crites 1992] [Rumsey and Lee-Rausch 2015] [Runyan and George-Falvy 1979] [Ruo and Sankar 1988] [Ruyten 1999] [Ruyten 2004] [Srinivasan et al 2020] [Saadeh et al 2026] [Sabatino et al 2023] [Sacks et al 1963] [Sakakibara et al 2021] [Salah et al 2018] [Saltzman and Ayers 1981] [Saltzman and Ayers 1982] [Saltzman et al 1999] [Santos and Mattos 2009] [Santos et al 2026] [Saric 1989] [Saric 2010] [Sarkar and Panneerselvam 1998] [Sarkar et al 2000] [Sarkar et al 2009] [Sarkar et al 2011] [Sarohia and Massier 1978] [Satran et al 1985] [Savin 2017] [Savin 2019] [Schmit 2012] [Schmitt et al 1983] [Schneider and Collicott 1997] [Schuelein 2008] [Schuman 2018] [Schwartz et al 2024] [Schweikhard 1966] [Schütte and Hummel 2025] [Scott et al 2015] [Secco and Martins 2018] [Segall and Gajdjis 1991] [Seiff 1954] [Seiff and Sandahl 1951] [Seraj and Martins 2023] [Serovy et al 1979] [Serpieri and Kotsonis 2015] [Shahid 2025] [Shan et al 2011] [Shang 2007] [Shankar and Malmuth 1982] [Shantz 1953] [Sheporaitis 1972] [Sheridan 1978] [Shih and Ding 1996] [Shirley et al 2014] [Shizawa et al 1996] [Signor and Borst 1986] [Silva et al 2006] [Sim 1976] [Sims and Carter 1981] [Simulation by Vortex Rings 1976] [Sinacori and Lange 1961] [Sinha 2007] [Sirbaugh 1983] [Slotnick 2014] [Smeltzer et al 1983] [Smith 1949] [Smith 1953] [Smith 1974] [Smith 1989] [Smith and Parsons 1970] [Smith and Shaw 1975] [Snyder and Erickson 1984] [Sobieczky 1998] [Song and Lv 2011] [Song et al 1995] [Sowyrda 1961] [Spadão et al 2026] [Spaid 1987] [Spaid 1990] [Spedding et al 2007] [Spillman 1992] [Spurlin and Lueck 1984] [Squire 1975] [Squires and Warmbrodt 1983] [Srivathsan and Rauleder 2023] [Stahara and Spreiter 1979] [Stahara and Spreiter 1980] [Stallings and Hartman 1981] [Stallings and Lamb 1981] [Staples and Nagati 1990] [Stargill 1983] [Stefko and Jeracki 1988] [Stefko et al 1987] [Steimle et al 2012] [Steinle et al 1999] [Stengel 1983] [Stewart 1985] [Stoican et al 2018] [Stone 1945] [Strand 1972] [Strand and Levinsky 1969] [Stringfield 1984] [Study on the Ground 2022] [Sun et al 2018] [Sundaram and Wu 1983] [Sutcliffe and Rennie 2016] [Sutton 1982] [Sutton et al 1982] [Swamy et al 1978] [Symington 1940] [Szodruch 1991] [Tabatabaei et al 2021] [Tafti et al 2014] [Tai 1990] [Tai et al 2024] [Takahashi et al 2023] [Tan and Hattori 2026] [Tang et al 2000] [Tayman and Walden 1998] [Telionis 1990] [Terry 1964] [Tetrault et al 2000] [Tetrault et al 2001] [The Airscrew Wind Tunnel 1983] [The stability of two-phase 1997] [The Swept - Wing 2021] [Theodorsen 1960] [Theodorsen and Nomicos 1961] [Thomas 1967] [Thomas and Lan 1991] [Tidbury 1945] [Tijdeman et al 1979] [Tijdeman et al 1979] [Torii and Matsuzaki 1992] [Tran-Luu and Solomon 2005] [Transonic flight test of 1994] [Transonic wind tunnel wall 1982] [Traub 2009] [Trimmer and Clark 1963] [Triplet 1983] [Triplett 1984] [Trolinger and O’Hare 1970] [Tsatsas et al 2025] [Tu 1992] [Tu 1992] [Tu 1994] [Tucker 1990] [Tucker and Quinn 1944] [Tuncer and Platzer 1998] [Turner 1982] [Ueki et al 2020] [Ueno et al 2004] [Ulbrich 2010] [Ulbrich and Boone 1998] [Ulbrich and Boone 2004] [Ulbrich and Steinle 1994] [Ulbrich et al 2014] [Ulbrich 1998] [Ustinov 2001] [Vaganov et al 2018] [Valenti and Yukish 2022] [van Arnhem et al 2022] [van der Maas 1959] [van Es 2002] [Varner 1986] [Varshney et al 2020] [Vatsa et al 1989] [Velasquez] [Velden 1997] [Venkataraman and Seiler 2016] [Venkataraman and Seiler 2019] [Venkataramanan and Dogan 2004] [Verhaagen 1997] [Verhaegen 1987] [Vermeersch et al 2015] [Verstynen 1974] [Vicini and Quagliarella 1998] [Visonneau et al 2015] [Vlachos and Telioinis 2003] [Vocke and Nunez 2016] [Vrabel 1988] [Vrdoljak 2003] [Wadia et al 1998] [Waggoner 1980] [Wagner 1985] [Wahidi and Troolin 2019] [Waite et al 2020] [Wakimoto et al 2021] [Waldmann et al 2016] [Walker and Berggren 1948] [Wallace 1952] [Wang 1980] [Wang 2026] [Wang et al 2007] [Wells et al 1981] [Wells et al 1982] [Wentz and Nyenhuis 1984] [Werner 2018] [Werner et al 2022] [Wey et al 2012] [Weyburne 2009] [Weyburne 2012] [Weyburne 2012] [Whalen and Bragg 2005] [Whitby 1991] [White 1963] [White 1993] [White 2004] [Whittaker and Doolan 2025] [Whittley and Garland 1961] [Wiberg et al 2014] [Widmayer and Tomassoni 1971] [Willard and Kranzler 1996] [Williams 1965] [Williams 2003] [Willis 1964] [Wilson 1981] [Winchenbach 1997] [Wind Tunnel 2022] [Wind Tunnel Interference on 1983] [Wind Tunnel Test Techniques 2024] [Windsor 1970] [Wing Design 2012] [Wing Design Considerations 2021] [Woodward 1968] [Woolard 1974] [Woolf 2012] [Wooten and Yechout 2008] [Wright 1962] [Wu 1978] [Wu 1986] [Wyborny and Requardt 1974] [Xie et al 2016] [Xiong et al 2021] [Xiong et al 2023] [Xu et al 2019] [Xu et al 2019] [Yamaguchi et al 1993] [Yamamoto et al 2012] [Yanagihara et al 1999] [Yang and Wu 2016] [Yang et al 2014] [Yasuaki and Egami 1999] [Ye et al 2021] [Yen 1978] [Yih et al 1952] [Yokozeki et al 2014] [Zannetti and Onofri 1984] [Zartarian 1956] [Zartarian and Hsu 1955] [Zeising and Gerhardt 1993] [Zeng and Kukreja 2013] [Zerihan and Zhang 2000] [Zhang] [Zhang et al 2000] [Zhang et al 2011] [Zhang et al 2023] [Zhang et al 2024] [Zhang et al 2026] [Zhao 1988] [Zhao 2021] [Zhao 2026] [Zhao 2026] [Zhao and Yang 2014] [Zhao et al 2014] [Zheng and Ramaprian 1993] [Zhou et al 2022] [Zhou et al 2025] [Zhu et al 2023] [Zhu et al 2026] [Zierten and Rettie 1977] [Zsoldos and Devenport 1992] [Ćurčić et al 2016] [Čečrdle et al 2022]

Blended and hybrid wing body configurations

The configuration itself, and the second largest cluster. Planform definition, centrebody structure, the non-circular pressure vessel, spanload and the trade against the tube and wing. The literature writes the configuration’s name both ways, and of the 636 titles in this cluster 115 hyphenate blended-wing-body or hybrid-wing-body while 253 write it as separate words, so a search of this literature must read a hyphen as a space.

636 records. [Abdullahi et al 2026] [Abnous et al 2017] [Abnous et al 2017] [Adamo 2023] [Adegbindin et al 2016] [Adhikari and Wei 2026] [Adler and Martins 2023] [AERO Dynamic Shape of 2014] [Ahn et al 2017] [Ahuja et al 2025] [Ahuja et al 2026] [Aleisa et al 2023] [Ali et al 2011] [Ali et al 2012] [Ali et al 2024] [Ali et al 2025] [Ali et al 2025] [Ali et al 2025] [Alipour et al 2022] [Almosnino 2016] [Ammar and Trépanier 2014] [Ammar et al 2017] [Ang and Ng 2026] [Antoniou et al 2025] [Arntz and Atinault 2015] [Asaro and Vos 2025] [Asaro et al 2025] [Atmaca et al 2026] [Aubeelack] [Aubeelack et al 2023] [Bahl et al 2020] [Bahr et al 2014] [Bai et al 2022] [Bainsla et al 2021] [Begin 1983] [Berger et al 2011] [Bertsch et al 2025] [Bhattarai et al 2026] [Bishara et al 2018] [Boeing flies blended wing 2008] [Boeing Phantom Works leading 2006] [Bolsunovsky et al 2001] [Bourdin et al 2007] [Brodsky and Luby 2013] [Brown and Vos 2018] [Buch and George M. 2010] [Buddhamatya et al 2026] [Burley et al 2014] [Burnside et al 2016] [Cai et al 2013] [Cai et al 2014] [Cai et al 2021] [Cameron and Cameron 1997] [Cameron and Princen 2000] [Campos and Marques 2021] [Carlsson 2003] [Carlsson and Kuttenkeuler 2003] [Carter et al 2009] [Chan 2019] [Chan et al 2024] [Chao et al 2017] [Chaplin 1990] [Chen et al 2019] [Chen et al 2024] [Chen et al 2026] [Chhabra et al 2015] [Chung et al 2024] [Chung et al 2025] [Clark and Gerhold 1999] [Colas et al 2018] [Computational Aerodynamic Analysis of 2016] [Contreras-Torres et al 2022] [Cook and de Castro 2004] [Cook and Hauser 2018] [Cui et al 2023] [Cui et al 2025] [Czech et al 2012] [Dakka and Johnson 2019] [Danowsky et al 2017] [Davis et al 2025] [Dehpanah and Nejat 2015] [Dela Peña 2024] [DeLaurier 2022] [Demourant and Ferreres 2013] [Denieul et al 2015] [Denieul et al 2018] [Deslich et al 2021] [Dickey et al 2016] [DiMaggio et al 2022] [Dimopoulos et al 2019] [Ding et al 2024] [Dinovitzer et al 2019] [Diyana Nasri Huang et al 2018] [Dominicus Danardono Dwi Prija Tjahjana et al 2021] [Donaldson et al 2011] [Dong et al 2024] [Dong et al 2024] [Dong et al 2025] [Doty et al 2014] [Wells and Olson 2011] [Du Cray et al 2025] [Durmus 2021] [Durmuş 2025] [Ebrahimi Fakhari et al 2024] [Ehlers et al 2011] [Einicke et al 2025] [Eleghasim et al 2026] [Experimental investigation of synthetic 2023] [Fairuz Izzuddin Romli et al 2023] [Felder et al 2009] [Felder et al 2012] [Felder et al 2025] [Feng et al 2026] [Fernandes and Maldonado 2024] [Fernandes et al 2025] [Fernando 2018] [Ferrar et al 2009] [Ferrell et al 2013] [Firdaus Mohamad et al 2010] [Flanagan et al 2020] [Flansburg 2017] [Flow Control and High-Lift 2016] [Flow Field Investigation of 2023] [Fremaux et al 1993] [From Tube and Wing 2013] [Fu et al 2022] [Fu et al 2024] [Fukuda and Takimoto 2014] [Galea et al 2003] [Gan et al 2014] [Gang et al 2019] [Gangoli Rao et al 2014] [Gao and Smith 2020] [Garcia et al 2016] [Garmendia et al 2015] [Garmendia et al 2016] [Gatlin et al 2012] [Gatto et al 2010] [Gauvrit-Ledogar et al 2018] [Gebbie et al 2005] [Gebbie et al 2007] [Geiselhart et al 2003] [Gern 2013] [Gern 2015] [Gilmore et al 2002] [Gingerich et al 2026] [Goldberg et al 2015] [Goldberg et al 2017] [Goldthorpe et al 2010] [Granzeier 2002] [Gray and Zingg 2024] [Gray et al 2021] [Gregory et al 2007] [Ground testing of X-48B 2007] [Gu et al 2022] [Gu et al 2023] [Guan 2013] [Guo and Thomas 2015] [Guo and Thomas 2015] [Guo and Thomas 2016] [Guo et al 2013] [Guo et al 2014] [Guo et al 2015] [Guo et al 2016] [Gupta and Khalid 2025] [Gupta and Khalid 2025] [Gupta et al 2016] [Guruswamy 1991] [Hakim and Choukri 2024] [Hakim et al 2025] [Hall et al 1999] [Handa and Srinivas 2022] [Haniš et al 2013] [Hansen et al 2007] [Hansmann and Stumpf 2025] [Hansmann and Stumpf 2026] [Hassairi and Abid 2021] [Hawley 1999] [He et al 2018] [Heath et al 2013] [Hill et al 2004] [Hong and Ma 2016] [Hooker 2014] [Howe 2001] [Huang and Wei 2025] [Huang and Zhang 2020] [Huang et al 2015] [Huber 1995] [Huber 2022] [Huber et al 2012] [Humphrey et al 2026] [Humphreys-Jennings et al 2019] [Humphreys-Jennings et al 2020] [Hutcheson et al 2014] [Hutcheson et al 2016] [Iniguez de Heredia and Friehmelt 2005] [Ishrak et al 2024] [Islam et al 2024] [Ito et al 2016] [Izadpanahi and Mardanpour 2018] [Izquierdo] [Jackson 2023] [Jackson and Buttrill 2006] [Jagtap et al 2024] [Jagtap et al 2025] [Joseph et al] [Jegley et al 2021] [Jia et al 2021] [Jiang et al 2019] [Jiang et al 2025] [Jianghao et al 2011] [Jiguang Li et al 2016] [Johnston 2016] [Joseph et al 2025] [June et al 2018] [Jung and Lowenberg 2005] [Jung Hoe and Nik Mohd 2014] [Kale and Pendharkar 2021] [Kania et al 2025] [Karimi Kelayeh and Djavareshkian 2024] [Karpuk et al 2020] [Karpuk et al 2023] [Kashitani et al 2015] [Katsurayama and Imamura 2015] [Kawai 2011] [Keidel et al 2019] [Keidel et al 2020] [Keller 2024] [Kerr 2025] [Khadiv et al 2025] [khan et al 2019] [Khandelia 2024] [Kim and Liou 2013] [Kim and Oh 2025] [Kim et al 2025] [Kim and Liou 2012] [Kim et al 2016] [Kimmel and Bradley 2004] [Kirner et al 2016] [Kitsios et al 2020] [Kleemann et al 2020] [Ko et al 2003] [Koster et al 2011] [Kotikalpudi et al 2018] [Kroo 1990] [Kucera and Hromčík 2013] [Kumar and Khalid 2017] [Kumar et al 2020] [Kumar et al 2020] [Kumar et al 2021] [Kumaran et al 2021] [Kummer et al 2012] [Kuntawala et al 2011] [Kuntjoro et al 2015] [La Rocca et al 2002] [Laban et al 2002] [Lampropoulos et al 2025] [Larkin and Coates 2017] [Latif et al 2017] [Lee et al 2008] [Lee et al 2018] [Legriffon et al 2023] [Leifsson et al 2013] [Lesalli and Cahyono 2020] [Li 2015] [Li 2024] [Li and Cai 2026] [Li and Guo 2013] [Li and Qin 2020] [Li et al 2017] [Li et al 2018] [Li et al 2023] [Li et al 2023] [Li et al 2026] [Lian and Wu 2018] [Liang et al 2016] [Liebeck 2003] [Liebeck 2008] [Liebeck et al 1998] [Liebeck 2004] [Liebeck et al 1996] [Liersch and Bishop 2018] [Lin et al 2008] [Liou and Lee 2010] [Liou et al 2016] [Liou et al 2017] [Liou et al 2019] [Liu and Whidborne 2021] [Liu and Zhang 2022] [Liu et al 2012] [Liu et al 2019] [Liu et al 2025] [Liu et al 2026] [Loechert et al 2018] [Lord et al 2016] [Loughban 2020] [Love and Kapania 2020] [Lovejoy 2006] [Lu et al 2012] [Lucky Bose et al 2024] [Luu 2025] [Lwin Moe and Aye Pyone 2019] [Lyu and Martins 2013] [Lyu and Martins 2014] [Lyu et al 2024] [Ahmad et al 2018] [Nasir et al 2022] [Ma and Wang 2009] [Ma et al 2019] [Mader and Martins 2010] [Madhanraj et al 2025] [Mahantesh Katagi et al 2015] [Maina et al 2005] [Mansor et al 2019] [Mardanpour and Hodges 2013] [Mardanpour and Hodges 2014] [Mardanpour and Rastkar 2017] [Mardanpour et al 2013] [Marske 1975] [Martín et al 2025] [Mascraenhas 2020] [Mastin et al 1996] [Johnson and Patel 2025] [Mayo et al 2016] [Meheut et al 2012] [Meng et al 2020] [Metin et al 2023] [Modeling and Control for 2015] [Mody et al 2010] [Mohamad et al 2012] [Mohammadi Farhadi et al 2018] [Mohan and Kumar 2023] [Mohan and Kumar 2026] [Mohan and Kumar 2026] [Mohan et al 2025] [Mohan et al 2025] [Moitra 1985] [Morris and Tigner 1995] [Mott et al 2025] [Movahhed and Hamed 2024] [Mukhopadhyay 2005] [Mukhopadhyay 2013] [Mukhopadhyay et al 2004] [Mukhopadhyay et al 2002] [Mulyanto and Nurhakim 2015] [Murray 1949] [Muñoz] [Mv et al 2023] [Nangia and Palmer 2002] [Nasir and Kuntjoro 2013] [Nasir et al 2010] [Nasir et al 2012] [Nasir et al 2014] [Nasir et al 2015] [Nazim et al 2026] [Nedilko et al 2026] [Ng and Spakovszky 2011] [Nickol 2012] [Nickol and McCullers 2009] [Nieto et al 2012] [Nishanth et al 2021] [Numerical investigation of aerodynamic 2023] [Okolo et al 2014] [Okonkwo and Jemitola 2022] [Okonkwo and Jemitola 2023] [Okonkwo and Smith 2016] [Ordoukhanian and Madni 2014] [Owashi et al 2017] [Oyama 2021] [Nishanth et al 2019] [Pachidas and Singh 2002] [Pambagjo et al 2001] [Pan and Huang 2018] [Pan and Huang 2019] [Pan et al 2017] [Pan et al 2023] [Pan et al 2025] [Panagiotou and Yakinthos 2017] [Panagiotou et al 2018] [Panagiotou et al 2021] [Panagiotou et al 2022] [Pao et al 2004] [Papamoschou and Mayoral 2011] [Parello] [Parisa et al 2020] [Pate 2013] [Patel et al 2024] [Patierno 1980] [Paudel 2016] [Paulus et al 2012] [Paulus et al 2013] [Pavlenko et al 2017] [Pei et al 2025] [Peigin and Epstein 2006] [Peigin and Epstein 2006] [Pellerito et al 2024] [Pellerito et al 2025] [Peng et al 2014] [Peterson and Grant 2011] [Petrenko and Gašparovič 2025] [Peña 2026] [Potsdam et al 1997] [Prakasha et al 2018] [Qi et al 2017] [Qi et al 2018] [Qi et al 2018] [Qi et al 2021] [Qian and Alonso 2018] [Qian and Alonso 2021] [Qin 2002] [Qin et al 2005] [Qin et al 2007] [Qiu et al 2024] [Qu et al 2011] [Qu et al 2017] [Quinlan and Gern 2016] [Rahman and Whidborne 2010] [Rajput et al 2014] [Rajput et al 2015] [Ranjan et al 2026] [Rasheed et al 2024] [Ratnayake et al 2011] [Razon et al 2023] [Regan 2008] [Reimann et al 2005] [Reimann et al 2006] [Reist and Zingg 2013] [Reist and Zingg 2014] [Reist and Zingg 2015] [Reist and Zingg 2016] [Reist et al 2019] [Rezazadeh Movahhed and Hamed 2026] [Richards and Tate 2023] [Richez and Bostock 2026] [Risch et al 2009] [Rizal E. M. Nasir 2023] [Rizzi et al 2013] [Roman et al 2000] [Roman et al 2003] [Roy 2009] [Roysdon and Khalid 2010] [Roysdon and Khalid 2011] [Rui et al 2007] [Ruseno 2021] [Rustagi et al 2018] [Saeed and Graham 2012] [Saeed and Graham 2015] [Saeed et al 2010] [Saeed et al 2011] [Saifuddin et al 2025] [Sargeant et al 2010] [Saucez] [Saucez and Boiffier 2012] [Savage et al 2026] [Schirrer et al 2013] [Schirrer et al 2013] [Schmidt 2016] [Schmidt 2016] [Schuette et al 2018] [Schuh et al 2016] [Scotzniovsky et al 2026] [Scuderi 2022] [Sears 1980] [Seebass 1997] [Sekulic et al 2025] [Sevant et al 2000] [Sgueglia] [Shao et al 2024] [Sharma and Hosder 2024] [Sharma et al 2012] [Shea et al 2016] [Shearwood et al 2019] [Shekar et al 2026] [Shen 2026] [Sheneshen and kamal 2025] [Sherman et al 2021] [Shi and Ma 2023] [Shi and Wu 2022] [Shi et al 2020] [Shi Jingping et al 2019] [Shin et al 2017] [Shuang et al 2016] [Siddiqui et al 2025] [Silva] [Singh et al 2016] [Sinha 2026] [Siouris and Qin 2007] [Sloan et al 1962] [Song et al 2014] [Song et al 2016] [Spellman 2003] [Staelens et al 2007] [Staub et al 2019] [Stroscher et al 2013] [Strüber and Hepperle 2006] [Sturm and Hepperle 2015] [Su and Cesnik 2009] [Suewatanakul et al 2022] [Sun et al 2026] [Sung et al 2025] [Sung et al 2025] [Surwase and Kumar 2025] [Susanto and Ahdan 2020] [Sutliff et al 2014] [Sutliff et al 2012] [Syed et al 2022] [Syed et al 2022] [Tahir et al 2026] [Tal and Karaman 2021] [Tal and Karaman 2022] [Tan et al 2014] [Tao et al 2016] [Tao et al 2017] [Tao et al 2018] [Taylor and Ratnayake 2011] [Taylor and Yoo 2011] [Taylor et al 2010] [Taylor 2009] [The specialized profiles for 2004] [Thomas and Guo 2017] [Thomas et al 2010] [Thomas et al 2010] [Thomas et al 2012] [Tigner et al 1998] [Tingting and Aijun 2014] [Tomac and Stenfelt 2014] [Tong et al 2009] [Torenbeek 1991] [Torenbeek 2016] [Torvik 1990] [Traas et al 2026] [Trittler et al 2008] [Tung and Song 2011] [Ul Haq et al 2026] [Valencia et al 2018] [Valencia et al 2020] [Van der Velden and Kroo 1994] [van der Voet et al 2012] [Vandervelden 1989] [Vasiliev et al 2014] [Velden 1997] [Velicki and Jegley 2011] [Velicki and Thrash 2010] [Velicki et al 2009] [Verstraete et al 2012] [Vicroy et al 2014] [Vicroy 2009] [Vicroy et al 2016] [Vile et al 2019] [Vile et al 2019] [Voss 2018] [Voss et al 2026] [Voß 2019] [Wakayama 1998] [Wakayama 2000] [Wakayama and Kroo 1998] [Wakayama et al 2003] [Wang and Feng 2026] [Wang and Qi 2021] [Wang and Wang 2012] [Wang and Zhao 2025] [Wang and Zhou 2022] [Wang et al 2019] [Wang et al 2020] [Wang et al 2022] [Wang et al 2022] [Wang et al 2023] [Wang et al 2024] [Wang et al 2025] [Wang et al 2025] [Wang et al 2025] [Wang et al 2026] [Wang et al 2026] [Wang et al 2026] [Waters et al 2013] [Weil Brenner et al 2012] [Weisshaar and Ashley 1973] [Weisshaar and Ashley 1974] [Westermayer et al 2013] [Weyl 1944] [Wick et al 2017] [Widhalm et al 2007] [Wienke et al 2023] [Wildschek 2014] [Wildschek et al 2013] [Wildschek et al 2013] [Wisnoe et al 2009] [Wisnoe et al 2015] [X-48B blended wing body 2008] [Xi and Zhao 2017] [Xie et al 2019] [Xie et al 2026] [Xin et al 2019] [Xu and Feng 2025] [Xu and Zhou 2015] [Xu et al 2013] [Xu et al 2019] [Xu et al 2022] [Xu et al 2026] [Yamada et al 2019] [Yan and Shi 2024] [Yan et al 2014] [Yan et al 2025] [Yang et al 2018] [Yang et al 2025] [Yi et al 2011] [Yi Zhu et al 2016] [Yingsong et al 2015] [You 2026] [Yu et al 2024] [Zakir et al 2024] [Zeng et al 2017] [Zha et al 2010] [Zhang and He 2026] [Zhang and Jia 2013] [Zhang and Meng 2019] [Zhang and Wang 2024] [Zhang and Zhao 2023] [Zhang and Zhou 2026] [Zhang et al 2009] [Zhang et al 2018] [Zhang et al 2019] [Zhang et al 2021] [Zhang et al 2025] [Zhao et al 2022] [Zhao et al 2022] [Zhao et al 2023] [Zhao et al 2026] [Zheng et al 2023] [Zheng et al 2026] [Zhu et al 2016] [Zhu et al 2019] [Zhu et al 2020] [Zou et al 2017] [Zou et al 2022] [Zou et al 2024]

Stall, departure and the uncommanded roll-off

The subject of the article’s central finding. Maximum lift, separation onset, wing drop, departure boundaries and recovery. This is the cluster the scaling argument bears on, since separation onset is the phenomenon a Froude-scaled model reproduces least faithfully and the one this aeroplane was built to find.

541 records. 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G and Balaji 2016] [Durham 1994] [Durston and Schreiner 1983] [Effect of forward swept 2010] [Ekaterinaris 1995] [Eko Sadewo and Sasongko 2017] [Ely and Herring 1978] [Ericsson 1983] [Ericsson 1984] [Ericsson 1984] [Ericsson 1987] [Ericsson 1988] [Ericsson 1991] [Ericsson 1996] [Ericsson 1996] [Ericsson 1997] [Ericsson 1997] [Ericsson 1999] [Ericsson and Reding 1970] [Ericsson and Reding 1976] [Ericsson and Reding 1982] [Ericsson and Reding 1985] [Fagley et al 2016] [Fagley et al 2017] [Faure and Leogrande 2020] [Favier et al 1987] [Feistel et al 1978] [Findlay and Guruswamy 2000] [Fischenberg 1995] [Forsythe and Woodson 2003] [Fouda and Taha 2022] [Frank et al 1994] [Freymuth 1990] [Fujimoto et al 1985] [Funk and McCormick 1991] [Fuykschot and Kooi 2004] [Gabel and Tarzanin 1972] [Gal-Or 1995] [Gallaway and Hankey 1984] [Gao et al 2025] [Gardner and Richter 2020] [Garmann and Visbal 2023] [Ge and Lan 1990] [Ghazi et al 2017] [Ghosh et al 2006] [Gilbert et al 1976] [Gnapowski et al 2021] [Goharshadi and Mirzaei 2022] [Goliszek and Goraj 2025] [Golmirzaee and Wood 2026] [Goman et al 1992] [Gopalarathnam and Segawa 2008] [Gordnier and Visbal 2004] [Gosselin] [Gousman et al 1991] [Grafton et al 1982] [Graham and Luskin 1946] [Graham and Yeow 1990] [Granasy 1995] [Grant et al 2017] [Grant et al 2018] [Green and Ott 2003] [Greenblatt 2010] [Greenblatt and Wygnanski 2002] [Greenewalt 1975] [Greenewalt 1975] [Grohsmeyer et al 1991] [Gross et al 2016] [Grote and Radespiel 2006] [Grove 2006] [Gunasekaran and Mukherjee 2016] [GuoJunPan 2026] [Gursul and Wang 2010] [Hall 2005] [Hall and Woodson 2003] [Hall and Woodson 2004] [Hall et al 2003] [Hammer et al 2021] [Hammer et al 2021] [Hanff and Jenkins 1990] [Hassan 2006] [He et al 2020] [Heald and Brassell 1976] [Hedlund 1988] [Heinrich et al 2022] [Heller et al 2001] [Hemsch 1989] [Hemsch 1990] [Hess] [Hess 1986] [Hettena et al 1992] [Heuschneider et al 2024] [Hipp et al 2016] [Hitzel 2017] [Hoadley and Pederson 2001] [Hodgkin and Wood 1998] [Hopwood et al 2023] [Howe 1983] [Hreha and Lutze 1983] [Hrynuk and Bohl 2020] [Hsu and Lan 1985] [Huang and Knowles 1990] [Huang et al 2026] [Hwang et al 1994] [Hyde et al 2018] [Identification of Departure from 2012] [Iliff 1980] [Iliff and Wang 1996] [Investigation on Jet Characteristics 2022] [Ishihara et al 2009] [Jahnke and Culick 1994] [Jamwal et al 2018] [Jarrah 1989] [Jing et al 2024] [Jirasek et al 2014] [Johnson and Lind 2009] [Johnson and Lind 2010] [Johnson et al 1981] [Johnson et al 1980] [Johnston and Hogge 1974] [Johnston and Hogge 1976] [Jordan and Hahne 1992] [Jun and Nelson 1987] [Kang and Kang 2001] [Karim and Acharya 1993] [Katz 1999] [Katz and Levin 1986] [Kaufmann et al 2016] [Kawazoe and Morita 2004] [Keller et al 2009] [Klein et al 1981] [Kobayakawa et al 1993] [Kok et al 2017] [Kokolios et al 2003] [Kroeger and Feistel 1976] [Krumenacker and Pellicano 1992] [Kubo et al 2010] [Kubota et al 1993] [Kumar et al 2025] [Kutschera and Render 1999] [Lackey and Hadfield 1992] [Lackey et al 1993] [Lamers 1974] [Lapins et al 1982] [Loftin 1954] [Lawrence et al 2001] [Le Clainche Martínez] [Lee and Gross 2024] [Lee et al 2024] [Lentink 2016] [Leos et al 2023] [Li and Scarano 2024] [Li and Yang 2017] [Li and Yang 2017] [Li et al 2021] [Li et al 2022] [Li et al 2025] [Li et al 2025] [Li et al 2026] [Lift and Stall 2021] [Lindsay 2021] [Lindsay and Walsh 2018] [Liu 2023] [Liu et al 2016] [Liu et al 2019] [Liu et al 2020] [Liu et al 2025] [Lohry et al 2013] [Lorber 1992] [Lorber and Carta 1991] [Lorber et al 1991] [Lowenberg and Lowenberg 1997] [Luchtenburg et al 2015] [Ludwig 1979] [Lutze et al 1993] [Ma et al 2025] [Macha et al 1972] [Magill et al 2003] [Mahale and Ananthkrishnan 2006] [Man and Fung 1995] [Manar and Jones 2017] [Marschalk et al 2021] [Martin and Hill 1989] [Marusak et al 2000] [Mathisen et al 2016] [McConnell 2004] [McCormack and Gleason] [McMillin et al 2003] [Medina et al 2019] [Mehra and Carroll 1980] [Meng and Jiang 2025] [Menner and Lavretsky 2026] [Meyer et al 1989] [Milillo 1972] [Millikan 1934] [Mitchell et al 1980] [Moore et al 1979] [Moosavi 2025] [Morelli et al 2013] [Mortensen 1995] [Motyka 1975] [Moul and Brown 1979] [Mukherjee et al 2003] [Murri et al 1983] [Müller et al 2022] [Narsipur et al 2016] [Nayman and Perez 2022] [Nelson and Arena 1993] [Nelson and Mouch 1978] [Ng and Malcolm 1990] [Ng et al 1993] [Nial 1972] [Niewoehner and Filbey 2005] [Numerical Study of Geometrical 2023] [Ogburn et al 1994] [Oliveira Silva and Wolf 2025] [Oliveira Silva and Wolf 2025] [On the role of 2018] [Ormsbee and Chen 1972] [Owens et al 2005] [Ozgören et al 2002] [Pabla 2021] [Pamadi et al 1994] [Paranjape 2022] [Paranjape 2023] [Patel and Smith 1996] [Patel et al 2002] [Patel et al 2006] [Patten 1988] [Paul and Gopalarathnam 2012] [Paul et al 2014] [Pavelka and Tatum 1980] [Payne and McConnell 2004] [Pedreiro et al 1996] [Pelikan 1983] [Perrier 1993] [Phillips and Alley 2007] [Pietrzak and Piechna 2013] [Pitkin 1943] [Pittman 1983] [Planeaux and Barth 1988] [Poplingher and Raveh 2023] [Poplingher and Raveh 2024] [Prach and Tekinalp 2014] [Prudnikov et al 1993] [Pucci 2012] [Pulimeno et al 2025] [Qi and Zhongke 2015] [Quan et al 2013] [Qureshi et al 2006] [Raghav and Komerath 2014] [Ramirez Zeigler and Avery 2026] [Ransom 1983] [Rao 1992] [Ray 1965] [Regenie et al 1992] [Reuster and Baeder 2000] [Reuster and Baeder 2001] [Richez 2017] [Richez et al 2020] [Richwine and Fisher 1991] [Riedelbauch 1992] [Rizk and Gee 1992] [Robertson et al 2014] [Rock 1985] [Rockwood et al 2019] [Rohith and Sinha 2017] [Rohlmann and Keye 2015] [Rom 1992] [Rom and Gordon 1988] [Roos 1996] [Rosen and Davis 1990] [Ross and Perkins 1994] [Ross et al 1991] [Roy and Mukherjee 2020] [Running et al 2017] [Sahin and Sankar] [Sahin et al 2000] [Salari and Roache 1990] [Salmon and Ahmed 2004] [Samuel and Mukherjee 2016] [Sanders 1973] [Santos et al 2024] [Sasaki et al 2009] [Schairer 1941] [Schuster and Byrd 2003] [Selvaraj and Sharma 2019] [Seraj and Martins 2021] [Sereez et al 2024] [Setoguchi and Kanazaki 2020] [Seyedtabaii and Delavari 2018] [Shah and Ahmed 2024] [Shah et al 2003] [Shen and Qin 1986] [Shi et al 2014] [Shi et al 2019] [Shields and Mohseni 2012] [Shigemi 1993] [Shumsky 2006] [Shumsky 2010] [Sibilski and Wróblewski 2012] [Silva and Wolf 2023] [Silva and Wolf 2024] [Silva and Wolf 2026] [Singh and Jategaonkar 1996] [Singh and Jategaonkar 1996] [Singh et al 1994] [Sinha et al 2013] [Sitz et al 1997] [Skillen et al 2013] [Smith and Chang 1970] [Snell] [Snell et al 1991] [Sogukpinar 2018] [Somers 2005] [Spakovszky et al 2000] [Stalford 1979] [Stalker 1935] [Stall Characteristics 2003] [Stall Speed 2021] [Stall Speed Measurement 2003] [Stall Testing 2021] [Stall, Approach, and Landing 2011] [Stenfelt and Ringertz 2013] [Sternberg et al 1994] [Stolt et al 2017] [Stone and Klinar 1948] [Stookesberry 2001] [Suarez et al 1993] [Sudharsan and Sharma 2021] [Sudharsan et al 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2018] [Zohar and Er-El 1988]

Reynolds number, scale effect and the transfer to full scale

The half of similitude that a free-flight model gives up. Scale effect on maximum lift, tunnel-to-flight correlation and extrapolation to full scale. Nine of these records match this survey’s subject terms only when a hyphen in the title is read as a space, among them a paper on correcting wind-tunnel pressure coefficients for Reynolds number effect.

523 records. [Abraham 1970] [Adrian and Balachandar 2001] [Agrawal et al 2024] [Ahlefeldt 2017] [Ahmad and Li 2022] [Airil] [Alexander and Griffin 1974] [Alexander et al 1973] [Algozino et al 2015] [Alhosseinihamedani et al 2019] [Amin and Das 2013] [Anyoji et al 2010] [Aono et al 2018] [Ariff et al 2015] [Arko and McQuilling 2012] [Asada and Kawai 2018] [Atef and El Baz 2023] [Athkuri and Nived 2026] [Effects of shear on 1980] [Ayers 1982] [Ayok 2026] [Baker and Squire 1982] [Balla and Vad 2022] [Balzer and Fasel 2010] [Bandyopadhyay and Gad-el-Hak 1994] [Barnaud et al 2019] [Batther and Lee 2022] [Becht and Knight 1995] [Beckwith 1974] [Bennington and Simpson 2004] [Benton and Visbal 2017] [Benton and Visbal 2018] [Benton and Visbal 2019] [Bertelrud 1998] [Bertelrud et al] [Beyers 1983] [Bigdeli and Monfared 2020] [Bodavula et al 2019] [Bohl and Hrynuk 2024] [Boschetti et al 2004] [Boughou et al 2023] [Bounecer and Bahi 2018] [Boutilier and Yarusevych 2012] [Brasseur 1994] [Braud et al 2024] [Brehm et al 2008] [Brendel and Mueller 1987] [Brendel and Mueller 1987] [Brion et al 2006] [Broeren et al 2017] [Brunner et al 2021] [Bucci et al 1997] [Bureau et al 2023] [Burt and Uselton 1974] [Bushnell 1998] [Bushnell and Greene 1991] [Busquet] [Carreno Ruiz and D’Ambrosio 2023] [Carter et al 2008] [Cebeci 1995] [Cebeci and McLlvaine 1989] [Cecchini et al 2026] [Chacin and Cantwell 2000] [Chamberlin and Blaha 1973] [Chandra et al 2024] [Chandrasekhara et al 1996] [Chen et al 2020] [Chien 1980] [Chien 1982] [Choudhuri and Knight 1995] [Choudhuri and Knight 1996] [Ciobaca and Dandois 2017] [Computations of Flow past 2021] [Conigliaro 1983] [Corlett et al 1980] [Cuvier et al 2014] [Darbandi et al 2006] [Davis 1968] [De Crombrugghe] [Della Rocca et al 2008] [Demoret et al 2020] [Deriat and Guiraud 1987] [Desabrais and Johari 1999] [Determination of the Reynolds 2012] [Djenidi and Antonia 1993] [Doerffer and Dallmann 1989] [Dong et al 2019] [Donovan and Selig 1989] [Donovan et al 2022] [Dougherty 1975] [Dougherty and Fisher 1980] [Drag, Scale, and the 2020] [Dróżdż and Elsner 2016] [Dróżdż et al 2021] [Duan et al 2020] [Dufau et al 2023] [Dwyer 1983] [Dyke 1971] [Effect of sting plunging 1978] [Effects of the Reynolds 2024] [Ekaterinaris et al 1994] [Eldridge-Allegra et al 2023] [Elfeky et al 2024] [Ellsworth and Mueller 1989] [Elsaadawy and Britcher 2000] [Elsaadawy and Britcher 2004] [Elsayed et al 2022] [Emmerson and Verstraete 2020] [Esabat et al 2025] [Evangelista et al 1987] [Evangelista et al 1989] [Fan et al 1993] [Fan et al 2019] [Fehrs and Helm 2025] [Fiore et al 2025] [Fleming and Simpson 1994] [Fleming et al 1995] [Foch and Toot 1989] [Fujita et al 1988] [Fukushima et al 2015] [Fukushima et al 2020] [Furlong and Fitzpatrick 1950] [Furlong and Fitzpatrick 1947] [Gao 2022] [Gao et al 2025] [Gargano et al 2011] [Gatto 2009] [Ghate et al 2026] [Ghia and Ghia 1997] [Gibson 2002] [Gloss and Sewall 1983] [Goodyer and Kilgore 1972] [Goodyer and Kilgore 1973] [Gopal et al 2026] [Gopalakrishnan and Tafti 2009] [Gopalarothnam and McGowan 2008] [Gowree et al 2023] [Grager et al 2011] [Grager et al 2012] [Gross and Fasel 2011] [Gross and Fasel 2013] [Große and Schröder 2009] [Guerreiro and Sousa 2012] [Gupta and Ansell 2018] [Gupta et al 2025] [Güler et al 2021] [Hall and Kern 1996] [Hall and Mohseni 2007] [Hammer and Shumway 2026] [Hanus et al 1991] [Hardy 1972] [Haucke and Nitsche 2013] [Hauser et al 2011] [Hayes et al 1999] [Hendrickson and Agarwal 2020] [Hess and James 1975] [HIGH Reynolds Number Flows 1992] [Hillewaert et al 2014] [Holdo 1993] [Holze et al 2002] [Honarmand et al 2019] [Hou et al 2026] [Howard and Kindelspire 1990] [Hoxey et al 1997] [Hsiao 1988] [Hu and Yang 2008] [Huang et al 2020] [Hutchings and Hall 2021] [Hutchings and Hall 2020] [Hutchings and Hall 2021] [Imamura and Tamaki 2020] [Inger 1989] [Islam et al 2009] [Islam et al 2024] [Ito 2009] [Ito et al 2018] [Itsariyapinyo and Sharma 2016] [Jackson et al 1982] [Nissen and Gadeberg 1944] [Jansen and Mueller 1983] [Jardin and Colonius 2018] [Jeon et al 2024] [Jeyapandian and Mukherjee 2014] [Jones et al 2017] [Jones et al 2018] [Ju et al 2026] [Junnai Zhai and Rebstock] [Kang 2025] [Kang et al 2015] [Kasibhotla and Tafti 2015] [Kawai and Asada 2013] [Kawasoe et al 2015] [Kay et al 2020] [Keadle and McQuilling 2013] [Kemp and Adcock 1982] [Kerho 2007] [Khan et al 2017] [Khedr et al 2021] [Khodadoust and Shmilovich 2007] [Khodadoust and Washburn 2007] [Kilgore 1982] [Kilgore and Dress 1984] [Kilgore et al 1974] [Kim and Chang 2009] [Kim and Chang 2010] [Kim et al 2009] [Kim et al 2015] [Komurasaki and Kuwahara 2006] [Korst et al 1994] [Kosgei 2017] [Kosugi and Hashimoto 2004] [Krishnan and Roy 2022] [Kruse et al 1977] [Kumawat et al 2025] [Kwon and Park 2005] [Kyeremeh et al 2023] [Ladson 1988] [Ladson and Hill 1987] [Landman et al 2022] [Langston et al 2025] [Langston et al 2025] [Larose and D’Auteuil 2008] [Law 1973] [Lazaro et al 2007] [Lazaro et al 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Flight control law design and envelope protection

The system that made an unstable aeroplane flyable. Control law architecture, gain scheduling, limiters and handling qualities. The X-48C needed new limiters because its handling qualities differed from the B model, which is the clearest published statement that the noise modification cost something.

500 records. [Abel and Newsom 1981] [Abrams and Weinstein 1974] [Advanced Aircraft Control 2026] [Aerospace - Flight Control] [Aerospace - Flight Control] [Aerospace - Vehicle Management] [Aerospace Active Inceptor Systems] [Air Force Test Pilot School Edwards Afb Ca 1981] [Air Force Test Pilot School Edwards Afb Ca 1988] [Air Force Test Pilot School Edwards Afb Ca 1988] [Air Force Test Pilot School Edwards Afb Ca 1988] [Air Force Test Pilot School Edwards Afb Ca 1988] [Air Force Test Pilot School Edwards Afb Ca 1988] [Air Force Test Pilot School Edwards Afb Ca 1989] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1991] [Air Force Test Pilot School Edwards Afb Ca 1992] [Aircraft Control 2016] [Aircraft Flight Control 2014] [Aircraft Flight Control Actuation] [Aircraft Flight Control Systems] [Aircraft longitudinal handling qualities 2011] [Al Tahtawi and Yusuf 2019] [Al-Shehabi and Newman 2002] [Alag and Duke 1985] [Alag and Kaufman 1974] [Alatorre et al 2023] [Alazard 2001] [Altunkaya et al 2024] [Amato et al 2022] [Anderson 1970] [Anderson 1960] [Application of dynamic flight] [Arent and Falatko 1992] [Ashkenas 1965] [Autenrieb 2025] [Automatic flight control system 2000] [Avanzini and Minisci 2010] [Bachelder and Aponso 2020] [Bachelder and Aponso 2020] [Bachelder and Klyde 2003] [Bachelder et al 2023] [Back-Up Flight Control System 1983] [Bailey 1984] [Ballouz and Chang] [Battipede et al 2004] [Bazill and Jenney 1970] [Beamer] [Beaufrere 1988] [Beh et al 2018] [Belkharraz and Sobel 2000] [Bennani and Looye 1998] [Berdjag et al 2010] [Berra et al 2017] [Bertolino et al 2024] [Bicego] [Bihrle 1970] [Bilendo and Shouzhao 2018] [Birckelbaw and Corliss 1992] [Black and Moorhouse 1979] [Blight et al 2018] [Blue et al 2002] [Bodson 2001] [Boeing Vertol Co Philadelphia Pa 1983] [Boothe et al 1974] [Bottasso and Montinari 2013] [Bouadi] [Boudreau 1976] [Boudreau 1977] [Bowes and Miller 1976] [Bradshaw et al 1985] [Breneman and Lower 1992] [Breul 1963] [Broderick] [Brown 1970] [Brown 2009] [Burcham and Burken 1994] [Burken et al 2009] [Burken et al 2010] [Cable Assemblies Aircraft, Proof] [Carlin and Blair 1983] [Carter and Cooper 1968] [Carter and Stephenson 1999] [Cartocci et al 2024] [Chalk et al 1969] [Chance Vought Corp Dallas Tx 1979] [Chapter 12. 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2016] [DiFranco 1971] [Dobos-Bubno and Hartsook 1977] [Dukes 1970] [Efremov et al 1998] [Ellis 1972] [Elsamra et al 2020] [Enciu et al 2025] [Enns 2003] [Estimation and Sensitivity in 2026] [Falkena et al 2010] [Fan and Hall 2014] [Feedback Flight Control 2026] [Ferreres and Puyou 2006] [Field et al 2002] [Fleck 1983] [Flight Control 2015] [Flight Control Actuation Systems 2025] [Flight Control Actuators] [Flight Control Design 2015] [Flight Control System Design 2008] [Flight control system design 2011] [Flight Envelope Awareness/Protection] [Flying Qualities 2003] [Fosdick 1970] [Franchi 2019] [Frost et al 2000] [Frost et al 2002] [Fujimori 2011] [Fujimori et al 1999] [Fujiwara et al 2003] [Fujizawa] [Funk 1975] [Gainer 1963] [Gang An et al 2018] [Gao et al 2021] [Gao et al 2021] [Gao et al 2021] [Gao et al 2021] [Gao et al 2021] [Gao et al 2021] [Gao et al 2021] [Garrec and Kubica 2005] [Gaylor 1984] [Gee et al 1976] [General Electric Co Schenectady Ny 1952] [Generally on automatic flight] [Gerken 1979] [Goetzendorf-Grabowski and Antoniewski 2016] [Goldstein 1982] [Graham 1986] [Grantham and Nguyen 1977] [Gray 2008] [Gray 1964] [Gregory et al 2011] [Ground and flight testing 2000] [Grudzinski and Tarabishy 2000] [Guerrero and Corliss 1991] [Guo and Liu 2012] [Ha 1990] [Hall 1969] [Handling qualities 2000] [Harper and Sardanowsky 1969] [Hart 1956] [Hart 1968] [Hartman 2019] [Hartmann et al 1979] [Hastedt et al 2022] [Herrmann and Ben-Asher 2016] [Hess 1990] [Hess 2004] [Hess 2005] [Hess 2005] [Hess 2006] [Hess 2010] [Hess 2012] [Hess 2013] [Hess and Peng 2018] [Hill 1987] [Himich and Kineyko 1981] [Hoh 1982] [Hoh and Mitchell 1983] [Hoh and Mitchell 2018] [Hoh et al 1981] [Hoh et al 2011] [Horn et al 1998] [Horowitz et al 1980] [Horsnell 1967] [Hoyt et al 1980] [Huang et al 2017] [Huang et al 2020] [Huff 1949] [Hyde and Glover 1993] [Industrial considerations for flight 2000] [Integrated Flight Instruments and] [Integrated Rudder and Brake] [Introduction The Flight Control 2017] [Ioannou and Rooney 1989] [Jackson and Coyle 1983] [Jackson and Patch 1968] [Jeanneau] [Jeanneau] [Jebakumar et al 2019] [Jeffrie and Rolston 1972] [Jenney 1979] [Jenney 1980] [Jenney et al 1982] [Jia-Hui et al 2025] [Jin and Wang 2015] [Johnson 1965] [Johnson and Redus 1968] [Johnston et al 1974] [Joos and Pfife 2012] [Juhasz et al 2015] [Kaden et al 2013] [Kai 2024] [Kaneshige et al 1999] [Kang et al 2013] [Kangyu et al 2025] [Karlsson] [Karpenko and Sepehri 2006] [Katayanagi 2001] [Katt and Raymont 1977] [Ke et al 2015] [Kempel 1971] [Kempel 1982] [Key 1971] [Khrabrov and Sidoryuk 2010] [Khrabrov and Sidoryuk 2013] [Khuat et al 2025] [Kineyko 1982] [Klyde et al 2007] [Kocurek et al 1997] [Kohnhorst and Magnacca 1980] [Kolesnikov 2005] [Konar et al 1974] [Kotfilia and Painter 1969] [Krachmalnick et al 1967] [Krings and Thielecke 2012] [Krishnakumar et al 2012] [Kubica and Livet 1994] [Lai et al 2017] [Langton 2006] [Larson 1986] [Lee and Dudginski] [Lee and Vining 2018] [Li and Chang] [Li et al 2009] [Li et al 2017] [Li et al 2018] [Li et al 2020] [Li et al 2025] [Lin et al 1998] [Linear Quadratic Flight Control 2026] [Liu and Xu 2026] [Liu et al 2009] [Liu et al 2022] [Liu et al 2025] [Liu et al 2026] [Lombaerts and Looye 2011] [Lombaerts et al 2010] [Lombaerts et al 2016] [Lu 2024] [Lusardi 2023] [Ma et al 2024] [Malaek et al 2006] [Manning and Gleason 1992] [Mant 1972] [Martin 1963] [Martin 1963] [Masaoka and Hashimoto 2024] [Masarati et al 2014] [Mattei and Scordamaglia 2008] [Matthews 1998] [McCuish and Caldwell 2018] [McKenzie 1973] [McMaster and Schenk 1973] [Mei et al 2024] [Meola et al 2013] [Methodology for Investigation of] [Mikami and Uchiyama 2015] [Miller 1968] [Mineck 1976] [Model-Based Approaches for Fast 2013] [Moncayo et al 2010] [Montgomery 1971] [Mooij 1985] [Moore et al 2024] [Moreira et al 2022] [Motyka and Reynolds 1971] [Musso et al 2024] [Nagata et al 1973] [Nagy and Kirsten 1976] [Napolitano et al 2001] [Nardi 1970] [Nettleton 1965] [Nguyen 2011] [Nguyen and Cord 1999] [Nield 1981] [Nikiforuk et al 1990] [Nonlinear model following control 1989] [Northrop Aircraft Inc Hawthorne Ca 1952] [Nuthi and Subbarao 2014] [Oelker and Brieger 2006] [Ogren et al 1974] [Ohara 1964] [Oosterom and Babuska 2001] [Optimization and Flight-Test Evaluation 2017] [Optimization and Piloted Simulation 2017] [Ostheimer and Giguere 1963] [Paine 1950] [Papa and Stoliker 1988] [Patel et al 2014] [Patterson 1968] [Patterson 1984] [Peng et al 2022] [Perhinschi et al 2005] [Petersen 1979] [Phillips] [Placement in Flight Control 2026] [Portapas and Cooke 2020] [Powers and Kier 1973] [Prasad and Unnikrishnan 2006] [Primary Flight Control Hydraulic] [Prosvirin and Kharchenko 2016] [Qian et al 2022] [Quantitative Design Requirements for 2017] [Queinnec et al 2006] [Rabenberg and Palarz 1983] [Rafi et al 2012] [Rang et al 1979] [Ratliff and Pagilla 2008] [Redeker 1987] [Research and Design of 2022] [Reynolds et al] [Rickard 1978] [Rinde 1969] [Rising 1982] [Ro et al 1992] [Robbins et al 2023] [Robinson] [Robinson 1968] [Robinson 1969] [Robinson et al 1989] [Rooney et al 1982] [Rosa et al 1974] [Roscoe et al 1975] [Roskam and Henry 1973] [Ross et al 1973] [Rotorcraft handling qualities design 2011] [Rustenburg 1972] [Ryu and Andrisani 2000] [Sadati et al 2011] [Sadovnitchii et al 1997] [Saetti and Rogers 2020] [Sagoo] [Sanders et al 2018] [Sanfilippo 1970] [Savelev and Neretin 2022] [Schmidt 1986] [Schmidt 1995] [Schreadley 1977] [Shafer et al 1989] [Shankar et al 2004] [Shen and Chen 2025] [Shen et al 2022] [Shi et al 2018] [Shin and Kim 2014] [Shives 1974] [Shmul et al 2018] [Shweyk and Weltz 2005] [Shweyk et al 2012] [Siddiqi and Abraham 1988] [Simsek and Tekinalp 2015] [Simulation Requirements for Flight 2017] [Singh et al 2017] [Sissingh 2015] [Slater 1974] [Smith 1967] [Smith 1977] [Smith 1991] [Smith 2023] [Smith et al 1971] [Smith et al 1973] [Solies 1995] [Sonneveldt et al 2011] [Sparks et al] [Steeb et al 1979] [Steer 2003] [Steer 2004] [Stengel 1973] [Stephan 2025] [Stich 2012] [Stolarik 2007] [Stougie et al 2024] [Strand and Ennis 2012] [Su 2014] [Subba Reddiar Pappu et al 2015] [Sun et al 2017] [Sun et al 2020] [Swarnkar and Kothari 2016] [Tang et al 2009] [Taranto and Abdulrahim 2023] [Tekles et al 2014] [Terminology for Flight Control] [Terminology for Redundant Flight] [Test Techniques for Flight 2021] [Tonon and Belluati 2018] [Urnes and Yeager 1991] [Validation and Verification Process] [Van Baelen et al 2018] [Van Gool and Weingarten 1981] [Vehicle Management Systems] [Vepa 2023] [Vinkler and Wood 1978] [Vinkler et al 1979] [Voigt et al 2019] [Vomaske et al 1978] [Vukobratović and Stojić 1986] [Waite et al 2021] [Waitman et al 2019] [Walker and Postlthewaite] [Waltz et al 1983] [Wang and Lei 2017] [Wang and Wu 2025] [Wang et al 2017] [Wang et al 2021] [Wang et al 2021] [Wang et al 2024] [Wang et al 2025] [Waszak et al 2002] [Weidemann and Leondes 1979] [Weiser 2025] [Well 2006] [Wells 2002] [Whitbeck and Hofmann 1978] [Whitbeck et al 1982] [Wichgers] [Wilson and Peters 2009] [Wilson et al 2014] [Wise et al 1999] [Woolley 1978] [Wu 2014] [Wu et al 2022] [Xargay et al 2010] [Xiaoxiong et al 2011] [Xin et al 2012] [Yang] [Yang and Morales 2021] [Ye et al 2007] [Yin et al 2020] [Yin et al 2023] [Yomchinda et al 2009] [Younkin 1968] [Yu and Jiang 2012] [Yu et al 2020] [Yu et al 2021] [Yue et al 2017] [Yue et al 2025] [Yuksek and Inalhan 2022] [Zaludin 2012] [Zamani Fekri and Mobed] [Zhang et al 2018] [Zhang et al 2020] [Zhang et al 2026] [Zhishuai and Lingling 2022] [Zhong et al 2021] [Zouaoui and Rami 2004] [Zuhri 2025]

Aircraft noise, shielding and the quiet configuration

The X-48C’s reason for existing. Airframe and engine noise, shielding by the planform, community metrics and the certification quantity. A configuration that puts its engines above a broad body has a noise argument no tube and wing can make, and the C model was built to fly it rather than compute it.

462 records. [A Potential Flow Model 1976] [A Preliminary Investigation of 1976] [A Review of Core 1975] [A. et al 2018] [Acoustic Characteristics of a 1976] [Acoustic Investigation of the 1975] [Aeroacoustics Jet Noise, Combustion 1976] [Aeroacoustics STOL Noise Airframe 1976] [Agarwal 2004] [Agarwal and Dowling 2005] [Agarwal and Dowling 2007] [Ahtye and Kojima 1976] [Aircraft Noise Airframe 2022] [Aircraft Noise Flight Operations 2022] [Aircraft Noise Flight Trajectories 2012] [Aircraft Noise Noise Sources 2012] [Aircraft noise prediction 1989] [Aircraft Noise Propagation 2012] [Aircraft noise sources 1989] [Airframe noise radiation from 1993] [Akatsuka 2024] [Akatsuka et al 2022] [Akatsuka et al 2025] [Ali et al 2016] [An Experimental Investigation of 1976] [An Experimental Study of 1976] [An Experimental Study of 1976] [Angelino et al 2019] [Appelbaum et al 2018] [Arntzen 2012] [Asada and Kawai 2026] [Asmatulu et al 2009] [Aujogue] [Balint and Balint 2015] [Ballard 1967] [Barbosa and Dezan 2013] [Barbosa and Dezan 2013] [Barton and Mixson 1980] [Bashforth 1981] [Bauer 1979] [Bauer and Munson 1977] [Bauer et al 2009] [Bauer et al 2012] [Baumann and Waggoner 2018] [Belyaev et al 2015] [Benek 1977] [Benito 1986] [Berge et al 1993] [Berman 1980] [Berton 2016] [Berton 2023] [Berton and Majjigi 2025] [Bertsch et al 2010] [Bhat and Gall 1975] [Birch 2023] [Bishop and Pearsons 1965] [Blacodon 2005] [Blacodon 2007] [Blandeau et al 2018] [Blech et al 2024] [Block 1979] [Block 1981] [Bloomer 1979] [Brehm et al 2015] [Broadbent 1976] [Brooks and Humphreys 1999] [Brown 2015] [Brown and Ahuja 1984] [Butzel 1981] [Butzel 1982] [Bychkov and Faranosov 2020] [Calder and Gupta 1977] [Cantos et al 2024] [Casalino and Barbarino 2011] [Casalino et al 2006] [Casper et al 2004] [Castner and Lake 2012] [Certified Aircraft Noise Data 2012] [Chapkis and Marsh 1977] [Chiba et al 2007] [Christophe et al 2023] [Clark et al 2021] [Clauss et al 1979] [Conticelli et al 1975] [Core Engine Noise 1975] [Core Engine Noise due 1976] [Coward and Griffiths 2024] [Cross and Watts 1983] [Cumming et al 2013] [Cutting engine noise 2007] [Czech et al 2022] [Dash et al 2003] [Davies and Moreau 2025] [Davy and Remy 1998] [Delfs 2024] [Denisov et al 2016] [Diagnostic Calculations of Airframe-Radiated 1976] [Diamond et al 2024] [Dieumegard] [Dimino 2024] [Dittmar 1986] [Dobrzynski 1980] [Dobrzynski 2010] [Dobrzynski 2010] [Dobrzynski and Heller 1977] [Dobrzynski et al 2000] [Dobrzynski et al 2002] [Doelling 1961] [Doelling and Bolt 1961] [Doelling and Bolt 1961] [Doherty and Butzel 1979] [Dougherty 1977] [Duct Acoustics Spinning Mode 1976] [Effect of Forward Speed 1976] [Eisenhut and Strohmayer 2026] [Electroacoustics. Instruments for measurement] [Elkoby 2005] [Elkoby et al 2007] [Engine Noise 1985] [Envia 2018] [Environmental Methods for Transport 2014] [ESDU Data Item helps 1999] [Ewert et al 2005] [Experimental Investigation of the 1976] [Experimental Studies of Noise-Shielding 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Fan Noise and Control 1976] [Farassat et al 2006] [Fares et al 2015] [Fares et al 2016] [Faulkner 1974] [Ferris and Khorrami 2024] [Ferris et al 2018] [Fethney 1975] [Fethney and Jelly 1980] [Fidell and Schomer 2007] [Fidell et al 1998] [Filler 1976] [Fink 1976] [Fink 1977] [Fink and Bailey 1980] [Fink and Schlinker 1979] [Fisher and Tester 2024] [Flight evaluation of three-dimensional 1972] [Flindell and Large 2024] [Carpenter et al] [Forward Velocity Effects on 1976] [Franken and Kerwin 1958] [Franzoni and Bliss 2000] [Fratello and Shearin 1975] [Fukushima et al 2014] [Gaeta et al 2009] [Gao and Qiang 2018] [Gasaway 1969] [Gasaway 1970] [Gerhold and Kim 1983] [Gibs et al 1976] [Giladi and Menachi 2024] [Girvin 2009] [Glover and O’Boy 2021] [Goddard 1991] [Goldschagg 2013] [Goodykoontz and Gutierrez 1977] [Gordon 1961] [Gorji-Bandpy and Azimi 2012] [Goyal et al 2025] [Graham et al 2014] [Greatrex and Brown 1959] [Greska et al 2004] [Grewal et al 2001] [Groeneweg 2024] [Groom et al 2025] [Grosche et al 1997] [Grosveld 1983] [Ground-Plane Microphone Configuration for] [Guo and Thomas 2026] [Guo et al 2002] [Guo et al 2019] [Hall 2024] [Hassan et al 2014] [Hayama et al 2013] [Hayden et al 1975] [Helffer et al 2014] [Heller and Dobrzynski 1977] [Hersh et al 1976] [Hirt 1991] [Ho et al 2011] [Holbeche and Hazell 1981] [Homans et al 1978] [Hou et al 2026] [House Noise-Reduction 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Tailless stability and control, and directional authority

What a configuration without a tail gives up. Directional stability, vertical surface sizing, yaw authority and the Dutch roll. A tailless aeroplane makes its yaw moments out of drag rather than out of a rudder on a long arm, which is the mechanism behind the weakness this article’s arithmetic then compounds for the X-48C.

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Transport aircraft design, sizing and fuel efficiency

What the configuration was for. Sizing, weight estimation, cruise efficiency and the fuel burn comparison that motivates the whole line of work.

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[Straub 1973] [Stringer et al] [Stroub 1989] [Svoboda 1999] [Takahashi and Lemonds 2015] [Takahashi and Lemonds 2015] [Tamboli 1956] [Taylor and Hunsaker 2023] [Taylor and Rogers 2014] [Toffol and Ricci 2023] [Tong and Naylor 2008] [Torenbeek 2013] [Torenbeek 2020] [Trade Studies and Sizing 2010] [Trial of a new 2008] [Ugwueze et al 2023] [Vallone] [VanLandingham and Hall 2023] [Velden 1997] [Vlasov 2022] [Vos 2019] [Vos 2019] [Wampler et al 1988] [Wang et al 2024] [Werner-Westphal et al 2008] [Whitford 1992] [Whitford 1994] [Wildermuth et al 1974] [Wildermuth et al 1974] [Winter et al 2021] [Worked Manned Aircraft Detail 2017] [Wortmann et al 2015] [Wrenn and Dovi 1987] [Wrenn and Dovi 1988] [Xie et al 2021] [Yang 2025] [Yang et al 2021] [Young 2010] [Yuhara et al 2016] [Zafi and Chakraborty 2023] [Zaimis et al 2024] [Ünal et al 2023]

Parameter identification and flight test technique

How the aeroplane was made to give up its derivatives. Multisine excitation, doublets, in-flight stability margin estimation and envelope expansion. A subscale vehicle makes this cheaper and more dangerous at once, because a cheap airframe can be risked and a fast one is harder to catch.

309 records. [Abate and Klomfass 2005] [Air Force Flight Test Center Edwards Afb Ca 1974] [Air Force Flight Test Center Edwards Afb Ca 1974] [Air Force Test Pilot School Edwards Afb Ca 1962] [Air Force Test Pilot School Edwards Afb Ca 1962] [Air Force Test Pilot School Edwards Afb Ca 1979] [Air Force Test Pilot School Edwards Afb Ca 1992] [Aksteter et al 1994] [Alford and Knarr 1999] [Anderson and Vincent 1985] [Armstrong 1977] [Asselin 2021] [Bach and Wingrove 1983] [Bajaj 2019] [Balcan et al 2026] [Banerjee et al 2026] [Bare-Airframe Identification from Data 2006] [Bare-Airframe Identification from Data 2012] [Barron 1967] [Bombois et al 2021] [Bombois et al 2025] [Boukhebouz et al 2021] [Branson and Fry 1994] [Brennan and McDaniel 1994] [Brieger et al 2008] [Brimelow 1970] [Bromberg and Hansen 1965] [Brown and Bradley 1981] [Bucharles et al 1990] [Burnett 2002] [Burton and Bischoff 1976] [Butts and Lawless 1990] [Carico 1998] [Carico et al 2005] [Chapter 2. Exploring the 2005] [Cheney 1988] [Clarke and Roskam 1982] [Cockrell and Doherr 1981] [Colin et al 2019] [Cooke 1980] [Coombe 1970] [Coopmans et al 2015] [Crama and Schoukens] [Crama and Schoukens 2001] [Crama and Schoukens 2001] [Crama and Schoukens 2002] [Crama and Schoukens 2005] [Cruz et al 1969] [Csurcsia 2022] [Cunningham and Hubbard 2018] [de Franca Arruda 1993] [De Jesus Mota and Botez 2009] [de Mendonça et al 2013] [Deepa and Gupta 2023] [Development of a Continuous 2012] [Dong et al 2024] [Dorobantu et al 2013] [Drag and propulsive efficiency 1990] [Duke and Lux 1983] [Dunlap and Porter 1971] [Enciu 2019] [Energy Approach To Performance 2003] [Eulrich and Rynaski 1980] [Evans et al 1994] [Everett and Oster 1994] [Exploring the Flight Envelope 2015] [Fechter and Mills 1988] [Figwer 2009] [Figwer 2013] [Figwer 2017] [Fletcher 1994] [Fletcher 2008] [Flight Test 2017] [Flight Test Maneuvers and 2008] [Flight TEST Manual 1959] [Flight Test Planning 2021] [Stoliker 2005] [Fry and Sage 1974] [Geerardyn et al 2012] [Ghosh and Raisinghani 2000] [Godwin et al 1964] [Gong et al 2018] [González et al 2021] [Granot and Sylman 1982] [Gratton 2018] [Grauer 2022] [Grauer and Boucher 2019] [Grauer and Boucher 2019] [Grauer and Boucher 2020] [Grauer et al 2021] [Grauer and Boucher 2018] [Grauer and Boucher 2018] [Gray 2016] [Green 1927] [Gritter 1992] [Hall et al 1972] [Hardier and Bucharles 2010] [Harris et al 2016] [Heeg and Morelli 2011] [Hein et al 2024] [Helicopter Flight Parameter Identification 1987] [Herrington et al 1966] [Hiliuta and Botez 2006] [Hill 1970] [Hoagg et al 2006] [Hodge and Audley 1983] [Hongchao Li et al] [Hosseini et al 2025] [Hull and Roger 1975] [Hulshoff et al 1996] [Hur and Valasek 2003] [Iliff and Maine 1983] [Iliff and Powers 1969] [Introduction to Stability and 2003] [Irwanto and Artono 2018] [Ishimoto and Ishimoto 1997] [Jategaonkar 2005] [Jategaonkar et al 2006] [Johnson et al 2025] [Jonkers and Mulder 1976] [Kaletka and Fu 1993] [Kallel and Kanoun 2022] [Kamal et al 2015] [Kammer 2025] [Kang et al 2021] [Karkar and Gökmenoğlu 2024] [Karpenko and Sepehri 2009] [Kay and Panagos 2004] [Kelly 1988] [Khoshlahjeh et al 2011] [Kimberlin 2003] [Klein 1978] [Klein 1989] [Klein and Morelli 1992] [Klyde et al 2004] [Kuehme et al 2014] [Kukreja 2008] [Kumar and Rao 2004] [Kumar et al 2008] [Kuppuswamy and Kiran 1981] [Larsson and Enqvist 2016] [Larsson et al 2020] [Lataire and Pintelon 2009] [Lebacqz 1974] [Lee 1985] [Lee et al 2007] [Leon et al 2009] [Level Flight Performance Flight 2003] [Level Flight Performance Jet 2003] [Li 2026] [Lichota 2023] [Lichota et al 2019] [Lichota et al 2019] [Lichter et al 2009] [Limitations and Flight Envelope 2017] [Liu et al 2018] [Londono and Leonhardt 2012] [Long 1968] [Longitudinal Control And Trim 2003] [Louali et al 2011] [Luo et al 2018] [Lykins and Keshmiri 2010] [Mallozzi et al 2014] [Manaï et al 2005] [Mancini et al 2014] [Mancini et al 2016] [Mannchen and Well] [Manning et al 1995] 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Marquart 1995] [Rees et al] [Remple and Tischler 2006] [Retzler et al 2022] [Roeser and Mönnich 2024] [Rosenberg and Schuch 1983] [Rucci et al 2023] [Runco and Benedict 2021] [Sandstrom and White 1961] [Saraswathi 2000] [Schmitz and Green 2012] [Schmitz and Green 2013] [Schneider et al 2012] [Schrader 2023] [Schumacher 1952] [Schuringa 1974] [Schwanz and Grimes 1980] [Schweikhard 1983] [Shi et al 2023] [Shixianjun et al 2006] [Siddiqui et al 2023] [Silva 2011] [Sim and Curry 1978] [Simmons 2022] [Simmons 2023] [Simmons et al 2023] [Simpson 1972] [Simpson 1979] [Soltmann and Hall 2017] [Song et al 2002] [Spangenberg and Friehmelt 2005] [Speyer and Crues 1985] [Srinathkumar et al 1995] [Stability margin 1988] [Stability Margin Computation 2018] [Stange 1959] [Steele and Vinnicombe] [Steele and Vinnicombe] [Steenken 1988] [Stottier 1995] [Sun et al 2013] [Swann et al 1981] [System In-Flight Testing 2010] [Szymanski et al 2025] [Tai et al 2023] [Taylor 2012] [Taylor et al 1992] [Thomas et 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Propulsion, airframe integration and installed performance

Engines on top of a body rather than under a wing. Integration, inlet behaviour, boundary layer ingestion and installed thrust. Thrust is also the quantity this article shows the model does not scale, which the propulsion literature frames.

288 records. 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Woodrey 1980] [Ford 1993] [Forliti and Diaz-Guardamino 2008] [Freeman and Klunk 2018] [Fuel cell demonstrator aeroplane 2007] [Furusawa and Kitamura 2020] [Gallagher 1968] [Garg 1993] [Garg and Mattern 1991] [Garg and Ouzts 1991] [Garg et al 1990] [Garnica and Takahashi 2017] [Gary and McDonald 2014] [Gilkey et al 1995] [Glasgow 1974] [Glover and O’Boy 2023] [Golladay and Gendler 1947] [Gu et al 2017] [Gubanov 2019] [Guidelines for the Integration] [Guidelines for the Integration] [Hahn 2012] [Haloulakos 1982] [Hamilton and Welge 1992] [Han et al 2026] [Han et al 2026] [Hartmann et al 2021] [Havey and Kline 1989] [Hawkswell et al 2022] [Helicopter Engine/Airframe Interface Document] [Henderson 1987] [Henderson 1990] [Hernanz et al 2015] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hiller Aircraft Corp Palo Alto Ca 1965] [Hines 1978] [Hirschel et al 2025] [Hirschkron et al 1979] [Hokenson 1986] [Hoogreef and Soikkeli 2022] [Imrak et al 2021] [In-Flight Thrust Determination] [In-Flight 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1977] [Richey et al 1983] [Robinson and High 1974] [Rodriguez 2007] [Rossow et al 1994] [Saghafi and Banazadeh 2009] [Salay and Elliott 1996] [Sallee 1973] [Schierman and Lowell 1992] [Schwartz 1975] [Scoppe 1973] [Shmelоv et al 2019] [Shovlin 1978] [Silva and Guimarães 2020] [Smeltzer et al 1974] [Smith 1966] [Smith 2014] [Smith et al 2004] [Staley 1975] [Stankowski et al 2016] [Stephan 2025] [Stuermer 2023] [Stuermer 2024] [Su et al 2025] [Sullivan 2002] [Surber and Sedlock 1978] [Sutliff 1973] [Tabei et al 1992] [Taylor 1971] [Tennant] [The Effects of Forward 1976] [Three-Dimensional Viscous Design Methodology 1986] [Thrust vector control 2026] [Time-Dependent In-Flight Thrust Determination] [Transducer 1987] [Tsai 1979] [Tsentis et al 2023] [Tsujikawa and Nagaoka 1990] [Tudosie 2018] [Uncertainty of In-Flight Thrust] [Vance 1973] [Veldhuis and Rentema 1995] [Venkatraman 2009] [Vinz and Raichle 2024] [Von Glahn et al 1974] [Vos 2019] [Vyatkov et al 2025] [Wahler and Elham 2025] 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High-lift devices, slats and separation control

The leading edge, which the X-48B tested in two configurations. Slats, flaps and separation control. The programme flew slats extended and slats retracted, which brackets exactly the behaviour the Reynolds mismatch makes least certain.

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Remotely piloted operation and the ground station

How the aeroplane was actually flown. Ground stations, displays, link behaviour and the pilot who is not aboard. This matters more here than in most of the series, because Froude scaling compresses the aeroplane’s time while leaving the pilot’s reaction time exactly where it was.

207 records. [Abdul Sathar Eqbal et al 2018] [Abeyratne 2016] [Abeyratne 2019] [Adelgren et al 2004] [Ale Isaac Khoueini] [Alexander 1979] [Army Scientific Advisory Panel Washington Dc 1977] [Aume et al 1976] [Ausserer and Harmon 2012] [Badole et al 2022] [Baigang 2024] [Barnwell et al 2003] [Battipede et al 2005] [Baumann and Gal-Or 1992] [Baumgartner et al 1979] [Becker et al 2011] [Benoit et al 2014] [Borst 1978] [Bruce et al 1998] [Burton and Hoburg 2018] [Cetinsoy 2015] [Chamitoff 1994] [Chamitoff 1995] [Chang and Laliberté 2023] [Chase and McDonald 2014] [Choi et al 2010] [Clark 1983] [Cordero et al 2014] [Corraro et al 2003] [Cunningham et al 2011] [D’yakonov et al 2018] [Dantsker et al 2018] [Dantsker et al 2020] [Dantsker et al 2023] [de Carvalho Bertoli et al 2016] [De Giorgi et al 2017] [Deets and Brown 1986] [Demir et al 2019] [Determination of External Power 2019] [Displaying trajectory of remotely 2011] [Edwards 1972] [Edwards 1981] [Eilertson 1975] [Eilertson 1975] [Ergocmen and Yavrucuk 2020] [Evolution of Human Systems 2016] [Fas-Millán and Pastor Llorens 2019] [Fitzgerald and Gingras 1996] [Flight performance of civil] [Fogel et al 1974] [Ford 1977] [Foster et al 2020] [Foy and Lawrence 2005] [French 1988] [Friedrich et al 2022] [Fulkerson et al 1980] [Fullmer et al] [Garcia-Hernandez et al 2017] [García-Hernández et al 2018] [Glizde and Urbaha 2019] [Glizde and Urbaha 2020] [Glīzde] [González Mendoza 2026] [González Mendoza 2026] [Gregory et al 1977] [Gunes et al 2019] [Guo and Xu 2000] [Guzel and Atesoglu 2014] [Gómez Rodríguez] [Gómez-Rodríguez and Cuerno-Rejado 2025] [Gómez-Rodríguez et al 2018] [Haaland and Sworder 1987] [Hall] [Hall 2014] [Hall 1992] [Harmats and Weihs 1999] [Hasan et al 2022] [Hicks and Durbin 2014] [Hinton and Eastlake] [Hobbs 2017] [Hobbs 2023] [Hoffelner et al 2023] [Holleman 1976] [Howard and Bray 1992] [Howard et al 1991] [Howse 2011] [Human Systems Integration for 2016] [Huntoon et al 1979] [Hyde and Massie 1993] [Initial Unmanned Aircraft Sizing 2014] [Initial Unmanned-Aircraft Sizing 2012] [Jameson 2009] [JanakiRam 1980] [Janakiram and Scruggs 1981] [JanakiRam and Scruggs 1982] [Jardin and Mueller 2007] [Jardin and Mueller 2009] [Jenn 1998] [Jie and Jung 2011] [Johnson et al 2011] [Jorris et al 2011] [Jun et al 2021] [Jung et al 2012] [Jung et al 2019] [Iain and Jones 2011] [Kearns 2018] [Kellett 1996] [Kellett et al 1996] [Khan and Nahon 2015] [Krohn 1988] [Krznar et al 2018] [Kubo and Suzuki 2008] [Kügler and Holzapfel 2020] [Lam et al 2020] [Larsen 1975] [Layton 1974] [Lee and Kim 2024] [Leite et al 2009] [Li et al 2025] [Li et al 2025] [Linehan 1996] [Lu 2017] [Manjarrez et al 2023] [Marshall] [Maughmer and Somers 1987] [McMinn and Jackson 2002] [McReynolds] [Mehta 2013] [Menhaj and Rajaei Salmasi 2000] [Merhav and Grunwald 1978] [Minor et al 2004] [Morris 1983] [Motter et al 2006] [Murray and Wild 2026] [Nachmani 2007] [Nelms et al 1976] [Nicholson et al 1988] [Nix et al 2009] [Olson 2015] [Orchard 2023] [Pan et al 2026] [Park 2019] [Paulson et al 1977] [Prudente and Cavalieri 2007] [Pugh et al 2020] [Pulk and Stolarik 1977] [Quraishi 1989] [Sadraey 2017] [Sarrafian 1984] [Sarrafian 1986] [Sato and Muraoka 2013] [Seaberg et al 1972] [Seanor] [Sekimoto et al 2020] [Selig 2010] [Shmelova et al 2017] [Simon and Rajesh 2022] [Sineglazov and Shmelev 2013] [Singh et al] [Singhal et al 2019] [Slapnicar] [Sridharan et al 2024] [Stiltner et al 2010] [Stone] [Stone et al 2006] [Słowik et al 2017] [Teng and Grant 2023] [Thato Elijah and Rui Vasconcellos 2026] [The Path Forward for 2016] [Torres et al 2011] [Training Issues for Remotely 2016] [Turnage et al 2019] [Tvaryanas 2006] [Tvaryanas and Maupin 2013] [Udroiu and Blaj 2016] [Urnes 2012] [Vandersteen 1987] [Varela Martínez] [Vengate et al 2016] [Vinkler et al 1980] [Wallace et al 2011] [Wang and Wang 2016] [Wang et al 2004] [Wang et al 2022] [Wanngoen et al 2020] [Wells 1995] [Welp et al 1975] [White 2005] [Wickens and Dixon 2002] [Wolfe] [Wortman et al 1975] [Xiaoxiao and Zhu 2025] [Xing and Yu 2012] [Xinghua 2018] [Xu et al 2019] [Yan et al 2024] [Yan et al 2025] [Yang 2021] [Yip et al 1990] [Yip et al 1991] [Yuan 2026] [Yuma Test Center Yuma Proving Ground Az 2008] [Zafirov 2010] [Zhang and Yu 2012] [Zhou and Huang 2022] [Ziemba et al 1989] [Zogopoulos-Papaliakos et al 2020]

Control allocation and redundant control effectors

Twenty surfaces and one pilot. Allocation, blending, daisy chaining and the overactuated problem. The X-48B carries twenty individually actuated trailing-edge surfaces, so allocation is not a refinement here but the means by which the aeroplane is controlled at all.

193 records. [Abrishami and Gong 2020] [Addington and Myatt 2000] [Ahmad et al 2008] [Ahmadi et al 2012] [Akram et al 2020] [Alwi and Edwards 2007] [Alwi and Edwards 2009] [Andersen et al 1996] [Antonakis and Biannic 2024] [Atay et al 2021] [Baggi et al 2020] [Battipede et al 2004] [Belsterling 1976] [Benosman et al 2007] [Bian et al 2018] [Bian et al 2019] [Binwen Lu et al 2016] [Bodson 2000] [Boskovic and Mehra] [Boskovic et al] [Boskovic et al 1998] [Buffington 1997] [Buffington 1999] [Buffington 1999] [Buffington et al 1999] [Bugday and Saetti 2023] [Burken et al 2001] [Casavola and Garone 2008] [Casavola and Garone 2010] [Cassaro et al 2018] [Chudoba and Cook 2003] [ChunSheng Liu et al 2012] [Cong et al 2023] [Control Allocation and Flight 2016] [Cordeiro et al 2024] [Cristofaro and Faleschini 2024] [Cristofaro and Galeani 2014] [Cristofaro and Johansen 2016] [Cristofaro et al 2015] [Cristofaro et al 2017] [Cui et al 2016] [de Vries and Van Kampen 2019] [Demenkov 2011] [Doman and Oppenheimer 2002] [Doman and Sparks 2002] [Dong et al 2016] [Dong et al 2024] [Duan and Okwudire 2019] [Durham et al 2016] [Frame-wise Control Allocation 2016] [Franze et al 2013] [Frost et al 2010] [Frost et al 2012] [Galeani and Sassano 2018] [Garmendia and Mavris 2016] [Gillard 1998] [Goodrich and Sliwa 1987] [Govoni and Cristofaro 2023] [Guan et al 2025] [Guo et al 2026] [Hallberg and Kaminer 1999] [Han et al 2025] [Hansen et al 2022] [Harkegard] [Harris et al 2022] [Henderson and Lavretsky 1999] [Himawan and Branjangan 2017] [Hou et al 2026] [Hu et al 2012] [Huang 2016] [Huang and Duan 2019] [Ijaz et al 2019] [Ijaz et al 2019] [Innocenti and Tonon 1988] [Jenkins 1973] [Jianjun Ma et al 2008] [Jianjun Ma et al 2008] [Jing and Ma 2025] [Jingping et al 2011] [Jo et al 2016] [Kang et al 2015] [Kang et al 2023] [Kara-Mohamed 2023] [Kefayat and Kamali 2024] [Kendall et al 2015] [Kendall et al 2017] [Khan et al 2012] [Lang and de Ruiter 2021] [Li and Ma 2014] [Li et al 2011] [Li et al 2012] [Li et al 2017] [Li et al 2018] [Li et al 2024] [Li et al 2025] [Li et al 2025] [Liang et al 2021] [Lin et al 2019] [Lingyu et al 2006] [Liu et al 2018] [Liu et al 2018] [Liu et al 2020] [Liu et al 2025] [Lou et al 2024] [Lu et al 2019] [Lu et al 2026] [Ma et al 2010] [Ma et al 2012] [Matamoros and de Visser 2018] [Acheson and Gregory] [Acheson et al] [Acheson et al] [Ming-Chao and Ju 2016] [Naskar et al 2015] [Naskar et al 2016] [Nelson and Durham 2002] [Nguyen et al 2018] [Ozdemir and Horn 2009] [Park et al 2017] [Pascucci et al 2017] [Pfeifle and Fichter 2021] [Pfeifle and Fichter 2023] [Prochazka et al 2018] [Qin et al 2023] [Qin et al 2023] [Rajput et al 2018] [Raney et al 2000] [Re 2014] [Renken 1985] [Sadien et al 2019] [Sadien et al 2020] [Saetti 2025] [Saetti and Horn 2018] [Sanghi et al 2022] [Scalera and Durham 1999] [Scordamaglia et al 2025] [Shayan and Van Kampen 2021] [Shearwood et al 2020] [Shearwood et al 2020] [Shearwood et al 2021] [Shi et al 2012] [Silva et al 2026] [Singh] [Singh et al 1999] [Sinha and Patra 2026] [Song et al 2014] [Stam and de Visser 2025] [Stephan 2025] [Tabassum and Bai 2022] [Tang et al 2025] [Tariq and Nahon 2020] [Nakamura-Zimmerer and Miller] [The Geometry of Control 2016] [Tohidi et al 2018] [Tohidy and Sedigh 2013] [Tol et al 2014] [Venkataraman and Doman 2001] [Vermillion et al 2007] [Vile et al 2020] [Virnig and Bodden 1994] [Wahler et al 2023] [Wakayama 2008] [Wang et al 2008] [Wang et al 2018] [Wang et al 2019] [Wang et al 2021] [Wang et al 2024] [Wang et al 2025] [Wilde et al 2008] [Williams et al 2025] [Xu et al 2020] [Yang and Gao 2020] [Yang and Shen 2007] [Yang et al 2009] [Yang et al 2010] [Ye et al 2009] [Yiming et al 2019] [Yin et al 2019] [Zaccarian 2007] [Zaki et al 2017] [Zelman et al 2023] [Zhan and Wang 2017] [Zhang 2017] [Zhang and Wang 2018] [Zhang et al 2007] [Zhang et al 2008] [Zhang et al 2025] [Zhang et al 2026] [Zhao et al 2026] [Zhen and Cui 2023] [Zhong et al 2009] [Zhu et al 2015] [Zou et al 2012]

Dynamic scaling, similitude and what a subscale model can answer

The keystone, and a smaller literature than the question deserves. Froude scaling, relative density, the mass and inertia relations and the free-flight model as an instrument. It is companion to the Reynolds cluster rather than separate from it, the first holding what is matched and the second what is surrendered.

189 records. [Aarons et al 2011] [Ahlefeldt and Quest 2014] [Akaryildiz et al 2024] [Allen et al 2015] [Ananda et al 2017] [Baggi et al 2022] [Balawi et al 2015] [Baldwin 2007] [Banazadeh and Hajipouzadeh 2019] [Bennett 1947] [Beyers et al 1997] [Bilanin 1987] [Bogos 2020] [Boisseau 1955] [Bovais et al 1992] [Bowles et al 2016] [Brandt et al 2019] [Brower 2024] [Buckley and Morfey 1983] [Buckley and Morfey 1984] [Burnside and Horne 2012] [Carraway 1988] [Chambers et al 2019] [Chambers 2010] [Chedrik et al 2004] [Comer et al 2024] [Comer et al 2026] [Constantin et al 2022] [Courtin et al 2020] [Cox et al 2012] [Croom et al 1988] [Croom et al 2000] [Cumming and Kramer 1966] [Cunningham et al 2008] [Dantsker 2024] [Dantsker 2024] [Dantsker and Mancuso 2019] [Dantsker and Selig 2015] [Davey and Ochoa-Cabrero 2023] [Stephens and Envia 2012] [Dean 2024] [Deitchman 1957] [Dick 2015] [Dickson et al 2010] [Dimensional Analysis and 2015] [Dimensional Analysis and Dynamic 2009] [Doherty] [Draper and Hewes 1948] [Droandi et al 2014] [Du et al 2024] [Du et al 2025] [Du et al 2025] [Eger et al 2013] [Elena 2026] [Elzinga et al 2014] [Eney 1981] [Fan et al 2024] [Free-Flight Models 1953] [Freidmann 2001] [Fremaux 1995] [Friedmann 1998] [Friedmann 2000] [Frostig and Simitses 2001] [Gonzales et al 2021] [Grana and Shanks 1952] [Guo et al 2017] [Hammer et al 2026] [Han et al 2015] [He et al 2021] [Hermes and Olivier 2013] [Hueschen 2011] [Hutter and Jöhnk 2004] [Harasani 2015] [Ivler et al 2019] [Iwakawa et al 2015] [Janna 2020] [Jarosław et al 2026] [Jayaraman et al 2022] [Johnson 1949] [Jordan and Bailey 2008] [Chambers 1988] [Jouannet et al 2008] [Jouannet et al 2012] [Keller et al 2026] [Kepler 1980] [Kittirungsi et al 2007] [Kobayakawa and Maeda 1978] [Kong et al 2023] [Korzun and Cassel 2020] [Kunwar and Chakraborty 2025] [Kunwar et al 2026] [Lam and Stollenwerk 1966] [Laumann 1966] [Lavan and Drummond 1987] [Lu et al 2015] [Lu et al 2016] [Luo et al 2014] [Luo et al 2016] [Mahdavi Talaromi and Abdollahzadeh 2026] [Mandal and Gu 2016] [Mas Colomer] [Mas Colomer et al 2017] [Massa and Cervenka 1995] [McClure and Sirbaugh 1991] [Mitcheltree 2003] [Monaco et al 2006] [Murch et al 2009] [Nadell et al 2022] [Nadell et al 2022] [Nadell et al 2023] [Nakamura and Oishi 2000] [Nepomuceno et al 2022] [Niemi and Bevillard 2015] [Obermark 2004] [Olejnik et al 2019] [Ouellette et al 2012] [Ouellette et al 2014] [Pan et al 2025] [Pieper et al 2018] [Potvin 2001] [Preisser 1979] [Preisser 1980] [Price and Earl A. 1981] [Price and Glidewell 1981] [Principles of Dynamic Similarity 2022] [Pulsonetti] [Pusztai et al 2024] [Ragheb et al 2013] [Raymer 2001] [Raymer 2001] [Repperger 1995] [Richardson et al 2014] [Robinson and Price 1975] [Rosen 1989] [Ross 1979] [Ruan and Aagren 2025] [Ruiz Garcia et al 2022] [Sadovnychiy et al 1998] [Saify et al 2025] [Scaling and Similitude 1638 2017] [Scherberg and Rhode 1927] [Schmitz et al 2024] [Sellers 2000] [Shalaby 2018] [Shawler 1981] [Shepheard 1965] [Shi et al 2018] [Shi et al 2023] [Similitude Relationships and Scaling 1992] [Similitude, Dimensional Analysis and 2007] [Simitses et al 2000] [Simmons and Ackerman 2026] [Simmons et al 2025] [Simon et al 2023] [Simon et al 2024] [Singleton and Yeager 2000] [Sobron 2018] [Song et al 2013] [Starkey et al 2012] [Straub et al 1984] [Suleman 2007] [Tai et al 2026] [Tian 1980] [Tian et al 2007] [Tierney et al 2019] [Tierney et al 2021] [Risch and Heersema] [Tosti 1961] [Turner 1965] [Uppoor et al 2026] [Viswanathan 2005] [Waltham 1997] [Wang et al 2019] [Wang et al 2020] [Wang et al 2020] [Wang et al 2020] [Wang et al 2021] [Wang et al 2025] [Wang et al 2026] [Ward et al 2026] [Warsop and Crowther 2019] [Williams 2021] [Williams et al 1994] [Wu 2006] [Yarlett et al 2000] [YiFan et al 2024] [Yue et al 2022] [Zhou 2023] [Zhu 2014]

Structures, materials and the airframe

The centrebody problem in general form. Loads, panels, composites and the non-circular pressure vessel that is the configuration’s hardest structural question.

174 records. [Abou Khalil] [Abumeri and Chamis 1996] [An et al 2018] [Anwar 2025] [Arney et al 1964] [Barsh 1944] [Barthelemy et al 1994] [Bauch and Lair 1970] [Baumgartner et al 1958] [Bazin and Fields 2015] [Belkharraz and Sobel 2001] [Bilger et al 1981] [Boudreault 1983] [Bramsiepe et al 2018] [Brewer 1953] [Brodersen 2002] [Browne 1990] [Burris and Bender 1969] [Butler 1972] [Carlin and Bevan 1986] [Castrichini et al 2018] [Cea and Palacios 2021] [Cella and Biancolini 2012] [Chen 2010] [Cheng 1982] [Chopra and Datta 2003] [Clay 2004] [Clay and Berens 1964] [Coleman 1952] [Coleman 1954] [Coleman 1957] [Coleman 1958] [Connelly et al 2024] [Cornell Aeronautical Lab Inc Buffalo Ny 1953] [Craddock 1973] [Daines 1966] [Danowsky and Schulze 2016] [Darden 1984] [Delgado Regis et al 2004] [Deneff 1973] [Dickinson 1953] [Doherty and Butzel 1979] [Douglas Aircraft Co Long Beach Ca 1962] [Dvorak et al 1947] [Ekquist 1965] [Ekvall and Young 1976] [England 1975] [Esposito et al 2026] [Failure of Aircraft Wing 2019] [Fanthorpe et al 2012] [Forte et al 2023] [Fu et al 2024] [Gallagher and Wei 2008] [Gerdes 2011] [Giessler and Nash 1971] [Glenn and Koch 1973] [Gottlieb 1987] [Green and Fernandez 1994] [Griffiths and Visser 2000] [Grover 1966] [Gurdal 2002] [Hanff and Huang 1991] [He 2015] [Heckl et al 1962] [Hepler et al 1973] [Heyong and Ye 2011] [Horton and Mayers 1965] [Horvath and Wrenn 2021] [Hwang et al 2003] [Itoh and Kobayashi 2000] [Johnson 1994] [Joo et al 2012] [Joo et al 2014] [Kain et al 1978] [Kaprilevskaya and Kozlov 2018] [Kautz 1972] [Kawazoe and Kato 2005] [Kenway and Martins 2014] [Kier 2005] [Konstantinovskaya et al 2024] [Kumar 2025] [Lee 1980] [Li et al 2024] [Lindsey 1977] [Liu and Sun 2025] [Lo et al 1995] [Maekawa et al 2007] [Magee and Taylor 1971] [Mahen 2026] [Mahulkar 2010] [Mangalam et al 2010] [Marchinski 1974] [Marsden and Price 2001] [Martin 1964] [Martinez et al 1987] [Masud and Khan 2015] [Matsuzaki et al 1987] [McDonnell Aircraft Corp St Louis Mo 1950] [Miller and Pollock 1955] [Milos 1998] [Milos and Squire 1996] [Tang 1970] [Mishler et al 1959] [Montel and Thielecke 2015] [Moon 1996] [Moosavian et al 2014] [Morote and Liaño 2012] [Mosby 1965] [Moshier 2006] [Nangia and Palmer 2007] [Newell 1939] [Norton 1990] [Norton 1990] [Norwood 1992] [Pak and Lung 2011] [Pan and Cheng 1995] [Panel Discussion Airframe and 1976] [Parikh et al 1994] [Park 2007] [Pechaud and Kim 2001] [Pretorius] [Rakowitz et al 2003] [Rand 1963] [Rhoads 1952] [Ricci et al 2016] [Roberts and Brown 1988] [Robinson 2004] [Robinson and Robinson 1950] [Rockwell 1994] [Rom 1992] [Rosende 1979] [Ross 1984] [Rotor Noise Panel Discussion 1976] [Smrithika 2025] [Sachs et al 1956] [Sachse 1998] [Schneider 1976] [Scott et al 2014] [Shih and Ding 1996] [Shlien 1991] [Siegel 1972] [Simon et al 2017] [Smith 1968] [Smith et al 1973] [Smrithika 2025] [Spearman 2007] [Supersonic transport wing minimum 1992] [Taha and Bauomy 2021] [Torenbeek 1972] [Tsushima et al 2022] [Ulbrich 2002] [Van Gaasbeek 1980] [Vaughan 1948] [Vaughan 2015] [Wada and Tamayama 2019] [Wei and Nie 2005] [Weiss et al 2013] [Weisshaar 1978] [What’s under the skin?] [What’s Under the Skin?] [What’s under the skin? 1999] [Whetstone and Robinson 1946] [Wilhem 1970] [Wing Loads 1996] [Xu and Song 2014] [Yamashiro and Livine 2009] [Yeager et al 1997] [Yen and Hsu 2007] [Yeo and Romander 2012] [Yihao et al 2024] [Zhang 2025] [Zhu and Li 2023] [Zientarski et al 2015] [Çelik and Yavuz 2016]

Rotorcraft, V/STOL and powered lift

Aircraft that lift on rotors, fans and deflected thrust. Helicopter and tiltrotor flight dynamics, vertical and short takeoff handling, powered-lift control and their flight test. They are kept because their stability, control law and flight test literature is the literature this article draws on, applied to another kind of aircraft.

86 records. [Alscher et al 1966] [Barrett 1952] [Bedford and Lowenberg 2006] [Bell Aerospace Co Buffalo Ny 1956] [Birckelbaw and Corliss 1992] [Bird 1970] [Bowes 1978] [Briardy et al 1970] [Brogan et al 1961] [Brown 1950] [Burks 1981] [Byrnes et al 1974] [Celi 2015] [Cohan and Hirsh 1966] [Creasey et al 1966] [Curtiss et al 1967] [Deel et al 1972] [Desvigne and Embacher 2025] [Deveaux 1965] [Doblhoff 1956] [Dominick and Watts 1967] [Dooley and Yeary 1979] [Duvivier and McCallum 1960] [Egerton and Fitzpatrick 1967] [Falcone et al 1974] [Finnestead and Connor 1969] [Finnestead et al 1970] [Gaonkar and Peters 1986] [Gaonkar et al 1981] [Goldberger 1966] [Gorton and Hoad 2002] [Gupta et al 1984] [Hargraves 1961] [Hayama et al 2021] [Head 1966] [Higher-Order Modeling of Coupled 2006] [Higher-Order Modeling of Coupled 2012] [Hirsh 1965] [Hoffstedt et al 1973] [Hughes and Wernicke 1974] [Jenkins and Marks 1975] [Judas and Deligiannidis 2013] [Liu et al 2023] [Lockheed-Georgia Co Marietta 1969] [Lopez et al 2021] [Louisse and Marshall 1974] [McPherson 1977] [Melton and Hall 1968] [Meyers et al 1968] [Miesner et al 2020] [Modelling Helicopter Flight Dynamics 2007] [Modelling Helicopter Flight Dynamics 2018] [Moschetta 2010] [Nagata et al 1968] [Nguyen and Webb 2025] [Nicholson and lowry 1966] [Oliveira] [Painter and Erickson 1984] [Parlier 1983] [Pieper 1965] [Pittsburgh Univ Washington Dc Research Staff 1966] [Piziali 1964] [Piziali and Duwaldt 1962] [Putman 1961] [Putman 1969] [Rais-Rohani and Baker 1994] [Rau and Greenwood 2022] [Rhodes 1969] [Roberts et al 1967] [Schrage and McKeithan 1989] [Schwartz and Wray 1969] [Shastry et al 2018] [Simon and Savage 1975] [Snyder 1950] [Sullivan 1993] [Taamallah 2015] [Tangler 1979] [The Boeing Canard rotor/wing 2004] [Turk and Watts 1964] [Vagianos and Rooney 1964] [Van Wyckhouse 1966] [Wang et al 2019] [Whitfield and Blackburn 1965] [Wyrick 1965] [Yamato et al 1988] [Yu and Sirohi 2026]

Aeroelasticity, flutter and flight vibration

The airframe as an elastic body in the airstream. Flutter prediction and suppression, aeroelastic tailoring, buffet and flight vibration surveys. The X-48B was dynamically scaled as a rigid body [Taylor 2009], so this is the half of dynamic similitude the aeroplane did not attempt.

82 records. [Aeroelasticity Problems in Compressible 2010] [Alyanak and Pendleton 2017] [Asher et al 1957] [Balachandran 2014] [Bennett and Abel 1981] [Bennett and Abel 1982] [Bolds 1961] [Bolds 1962] [Brenner 2001] [Brown et al 1980] [Byreddy et al 2003] [Cazier and Kehoe 1986] [Cea and Palacios 2023] [Chuban 2005] [Clarke et al 2005] [Davis and Hoffler 2009] [Deangelis 1981] [Dowell 1996] [Dugundji and Ghareeb 1965] [Engelbrecht] [Extended Models of Large 2012] [Farhat 1999] [Farhat 2001] [Ferede 2022] [Flight Dynamics of Elastic 2014] [Fujino et al 2003] [Gonzalez et al 2023] [Grauer and Boucher 2017] [Graves et al 2003] [Heidersbach et al 2024] [Herrmann and Nemat-Nasser 1966] [Hu et al 2009] [Jones 1970] [Jones and Nisbet 1976] [Kawakami et al 2008] [Kayran 2007] [Kehoe 1988] [Kehoe and Freudinger 1994] [Keye and Rudnik 2009] [Kim et al 2009] [Lee et al 1991] [Lesoinne 2007] [Lind 2003] [Lind 2003] [Mukhopadhyay 1995] [Nash et al 1975] [Neuert and Dinkler 2020] [Newsom and Pototzky 1981] [Nguyen et al 2018] [Oz 1998] [Pachikara and Lind 2012] [Pancini dos Santos and Marques 2024] [Raveh 2011] [Richter and Patil 2010] [Rimer et al 1983] [Rimer et al 1984] [Rimer et al 1984] [Sarıgül and Erbay 2026] [Sevy and Earls 1970] [Spivey et al 2020] [Sudha et al 2018] [Tang and Dowell 2000] [Tang and Dowell 2001] [Tantaroudas et al 2015] [Tao et al 2023] [Thomas 1961] [Thomas 1961] [Ting et al 2017] [Tran and Lind 2010] [Triplett 1980] [Vepa 2023] [Vijayakumar et al 2014] [Wang et al 2018] [Weisshaar 1979] [Winther et al 2000] [Wu 1975] [Yang and Wan 1978] [Yates and Bennett 1972] [Yates et al 1983] [Yoo et al 2002] [Zettel et al 2023] [Zimmerman and Weissenburger 1964]

Flight test instrumentation, air data and test data processing

How a flight test measures what it measures. Air data probes and angle-of-attack vanes, data acquisition and recording, and the processing and management of test data. The X-48B carried two air data booms measuring total and static pressure, static temperature, angle of attack and sideslip [Risch et al 2009], and every derivative identified in flight rests on them.

69 records. [Air Force Test Pilot School Edwards Afb Ca 1967] [Air Force Test Pilot School Edwards Afb Ca 1967] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1993] [Aircraft and Flight Test 2021] [Angle of Attack Indicator 1960] [Arévalo Nogales 2020] [Bach and Parks 1987] [Bach 1980] [Bever 1992] [Bleimeyer 1981] [Bogue 1992] [Bowen et al 1985] [Brooks 1986] [Che et al 2021] [Chen et al 2021] [Day and Guthrie 1958] [Dean 1942] [Design and Installation of] [Dodgson 1973] [Douglas Aircraft Co Inc Santa Monica Ca 1963] [Emerson et al 1955] [Flight TEST Procedures for] [Freuler and Hoffmann 1977] [Garman and Andrisani 2003] [Gibson 1981] [Gracey 1980] [Gregory and McCrink 2016] [Hensley 1994] [Hermann et al 1984] [Ivanković et al 2023] [Jain et al 2019] [Jann and Greiner-Perth 2009] [Karam 1975] [Kaye 1983] [Kish et al 2017] [Knighton 1992] [Kohn and Pangilinan 1986] [Large et al 1981] [Leckman and Bennett 1978] [Liu 2023] [Luo and Katz 2017] [Martin 1978] [Martos and Rogers 2018] [McElreath 1972] [Methods for Reducing Data 2003] [Miniaturised Inertia! Measurement Unit 2005] [Monteil 2024] [Moul and Taylor 1981] [Moum 2010] [Naval Air Test Center Patuxent River Md 1963] [Oosterom and Babuska 2006] [Pawlak 1994] [Pommier-Budinger et al 2016] [Previati et al 2012] [Redeker and Voersmann 1988] [Rimmer 1952] [Rogers 2019] [Sanderson 1965] [Schafer 1962] [Stouder 1981] [Strader et al 2016] [Vaughn and Lindsay 1988] [Ward and Berge 2012] [Ward and Binford 1986] [Whitmore 1988] [Wilkin Perry 1943] [Yokota et al 2021] [Zhai et al 2024]

Flight test programmes, organisations and their history

The institutions and campaigns of flight test. Programme overviews of named aircraft, test centres, ranges and test management, and the history of research flight. The X-48B’s own flight test campaign is among them, together with the Environmentally Responsible Aviation project from which the X-48C’s noise objective came [The Environmentally Responsible Aviation project, a technology development project].

61 records. [Adolph 1981] [Air Force Flight Test Center Edwards Afb Ca 1970] [Air Force Flight Test Center Edwards Afb Ca 2002] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Proving Ground Center Eglin Afb Fl 1954] [Air Proving Ground Center Eglin Afb Fl 1955] [Army Aviation Board Fort Rucker Al 1964] [Broughton 1978] [Carico 1995] [Cook 1981] [Cosenito 2010] [Cusimano and Johnson 1994] [Dawson 2015] [Dwyer 1994] [Enzinger 1988] [Eppley 1963] [Experience Gained During Development 2010] [Gentry 1968] [Hart 1992] [History of Supersonic Transport 2020] [Hoadley 1988] [Immenschuh 1988] [Jann et al 1999] [Lux-Baumann and Burkes 2005] [Jordan 1974] [Kempel and Painter 1994] [Kennedy 1986] [Lang 1981] [Manning et al 1992] [Mascitti and McLean 1976] [McTigue and Ryan 1968] [Mertaugh 1998] [Meyersburg 1968] [Miller 1973] [Morgenfeld 1992] [Morger 1988] [Nakadate 2005] [Nicholson 1985] [O’Connor 1982] [Redelinghuys et al 2015] [Rhea and Moore 1988] [Rice 1946] [Rice and Hazlwood 1994] [Roberts 1988] [Roberts 1988] [Robertson and Hartfield 1992] [Shields 1981] [Silberg and Haas 2011] [Svendsen 1994] [The Environmentally Responsible Aviation project, a technology development project] [Thornton 1994] [Thornton and Lamy 1992] [Townsend and Phillips 1955] [Townsend and Phillips 1956] [Veletas 2026] [Wagner 1973] [Wang 2024] [Williams 1981] [Wissler 1981] [Woodman 1971] [Wright 1987]

The atmosphere and the flight condition

The medium, named rather than assumed. Standard atmosphere properties, density altitude and the speed of sound. The kinematic viscosity ratio and the relative density readings in this article are taken from the standard atmosphere, so the literature that defines it belongs in the survey.

60 records. [A Properties of Standard 2006] [A Standard Atmosphere 2022] [Air Force Test Pilot School Edwards Afb Ca 1962] [Altmann 2011] [Analysis of Gust-Response Flight-Test 1988] [Appendix A Standard Atmosphere 2021] [Appendix A. The Standard 2011] [Appendix B Properties of 2003] [Appendix E Standard Atmosphere 1979] [Appendix E Standard atmosphere 2004] [Approximations for the thermodynamic and transport properties of high-temperature air] [Ashburn et al 1970] [B-34. U. S. Standard 1963] [Buck et al 2004] [Buck et al 2005] [Definition of the standard 1954] [Dennis P. Dykstra 1980] [Herbert] [ICAO Standard Atmosphere 2021] [International Standard Atmosphere 2010] [Kang et al 2023] [Kang et al 2023] [Kaushik 2018] [King-Hele 1964] [Kurzke and Halliwell 2018] [Lehman and Kaplan 1965] [Minzner et al 1976] [Other publications Reference/standard atmosphere 1987] [Pelton and Hannah 1976] [Peters 1977] [Pressures and Temperatures for 2000] [Properties of the U.S 2014] [Properties of the U.S 2024] [Report No. 538, altitude-pressure 1935] [Space environment natural and] [Standard Atmosphere 1997] [Standard Atmosphere 2005] [standard atmosphere 2014] [Standard Atmosphere 2023] [Standard Atmosphere 2024] [Standard atmosphere chart 1927] [Standard atmosphere chart supersedes 1927] [Standard Atmosphere Data 1992] [Standard Atmospheric Profilesa aSource 2002] [Sutherland 1893] [Minzner 1976] [The Flight Environment Standard 2021] [The International Standard Atmosphere 2017] [The international standard atmosphere 2026] [The NBS-NACA tables of thermal properties of gases] [The Standard Atmosphere 1920] [The Standard Atmosphere 1964] [The Standard Atmosphere 1976] [Turns and Kraige] [U. S. Standard Atmosphere 1963] [U.S. Standard Atmosphere, 1976] [US Standard Atmosphere Model 2014] [Vaughan 2003] [Yaroshevsky 2010] [Zuppardo 1993]

Flight mechanics and aircraft performance

The equations the scaling relations are written in. Equations of motion, steady, gliding and turning flight, range, endurance and performance methods, mostly as chapters of reference texts. The Froude ratios in this article are dimensional consequences of these equations, which is why their reference statements belong in the survey.

57 records. [Aircraft Cruise in Steady 2011] [Aircraft Cruise in Steady 2011] [Aircraft Equations of Motion 2003] [Aircraft Equations of Motion 2014] [Aircraft Equations of Motion 2022] [Aircraft Maneuvers and Flight 2011] [Aircraft Maneuvers and Flight 2011] [Aircraft Mechanics 2026] [Aircraft Model 2025] [Aircraft Models 2012] [Aircraft Operating Envelope 2010] [Aircraft Performance 2003] [Aircraft Performance 2014] [Aircraft Performance 2026] [Aircraft Range and Endurance 2011] [Aircraft Range and Endurance 2011] [Aircraft Steady Gliding Longitudinal 2011] [Aircraft Steady Gliding Longitudinal 2011] [Aircraft Steady Level Turning 2011] [Aircraft Steady Level Turning 2011] [Aircraft Steady Longitudinal Flight 2011] [Aircraft Steady Longitudinal Flight 2011] [Aircraft Steady Turning Flight 2011] [Aircraft Steady Turning Flight 2011] [Appendix A Relevant flight 2011] [Ashley 1967] [Baghiyan 2021] [Barnard 2004] [Buell 1970] [Complete model of aircraft] [Computational Flight Dynamics 2016] [Cook 2000] [Flight dynamics � Vocabulary] [Flight Envelope 2021] [Flight Envelopes 2012] [Flight Vehicle Performance 2001] [From Steady Flight to 2011] [From Steady Flight to 2011] [Hightower 1985] [Lynch 2001] [Krishnamurthy and Luckner 2017] [Linear Flight-Dynamics Analysis 2023] [Miller and Koch 1985] [Nominal aircraft dynamics] [Northrop Aircraft Inc Hawthorne Ca 1953] [Piloted Aircraft Performance 2004] [Rigid-Body Flight Dynamics 2026] [Schwanz 1972] [Sinha and Ananthkrishnan 2017] [Sinha and Ananthkrishnan 2017] [Sinha and Ananthkrishnan 2017] [Stephan 2025] [Streby 1990] [Takeoff and Landing Theory 2003] [Thelander 1965] [Wenxuan 1991] [Young 2010]

Unconventional wings, joined, oblique, swept forward, morphing and flexible

Configurations that, like the blended wing body, depart from the tube and wing. Joined, oblique, forward-swept, variable-sweep and morphing wings, wing-in-ground-effect craft and flexible-wing and parafoil gliders. They are this literature’s other experiments in configuration, kept apart from the blended wing body cluster because none of them is one.

44 records. [Ahad and Graham 2007] [Beatty et al 1977] [Bird 1973] [Blair et al 2008] [Bonnema and Smith 1988] [Clyde et al 1984] [Design of Unique Aircraft 2024] [Dizdarevic and Dizdarevic 2022] [Folding Wing Flight Test 2018] [Further development and flight 1994] [Goddard and Eastgate 2010] [High-Altitude Long-Endurance HALE Sensor 2026] [Islam et al 2025] [Kentfield and Spragins 2004] [Kress 1983] [Krone 1980] [Krone 1980] [Lange and Moore 1979] [Lazos 2005] [Leonard 2001] [McMurtry et al 1981] [Nangia and Palmer 2007] [Nicolaides 1976] [Oblique Wing Aircraft 2020] [Painter 1983] [Powers et al 1992] [Rasmussen et al 2006] [Ro et al 2010] [Ryan Aeronautical Co San Diego Ca 1962] [Ryan Aeronautical Co San Diego Ca 1963] [Sakamoto and Cota 1965] [Smith and Srokowski 1983] [Smith et al 1987] [Spacht 1980] [Spinning Aircraft and Nonspinning] [Trancossi et al 2016] [Traub 2024] [Vale et al 2014] [Variable sweep wing design 1980] [Vishwanathan] [Ward et al 2011] [Willan 2011] [Xiong et al 2019] [Yamazaki and Kusunose 2014]

Flight simulation and simulators

The ground instrument that stands in for flight. Simulation models and their exchange, simulator fidelity and motion requirements, and in-flight simulation. Every X-48B mission was rehearsed in the simulation mode of its ground control station before it was flown [Risch et al 2009], and the programme reports the aeroplane as closely matching simulation in up-and-away flight and landing [Vicroy 2011].

43 records. [Abbott et al 1982] [Aircraft Simulation Model 2022] [Almanza et al 1994] [Branson 1994] [Brunner 1996] [Carlson et al 1980] [Chen et al 2008] [Crosbie et al 1981] [Evans and Schilling 1983] [Flight Simulation 2016] [Harding and Bass 1990] [Hayden 1970] [Hofmann and Riedel 1979] [Jackson and Hildreth 2002] [Jackson and Hildreth 2006] [Kurtzberg 1963] [Math Model Assembly and 2023] [McIntyre 1963] [Moormann] [Morlang and Strassburger 2025] [Pan et al 2014] [Rawson 1963] [Recommended Practice When Flight 2021] [Rediess and Melton 1994] [Research and Analysis on 2022] [Richards and Dismukes 1982] [Riedel 1979] [Sato 2006] [Simulation in support of 1988] [Spitzer et al 1972] [Staley 1976] [Standard Flight Dynamics Model 2011] [Swanson et al 1992] [Taghizad et al 2021] [Taylor et al 2025] [Tischler and Tobias 2016] [Wang and Song 2025] [Warner 1995] [Weingarten 2004] [Woltkamp et al 1988] [Zapico et al 2008] [Zhixin 2022] [Zhixin 2022]

Where the Framing Breaks Down

The reference vehicle’s weight is derived, and the one quoted figure is a round number in a magazine. The figure of 854,875 pounds comes from inverting the cube of the scale ratio on the model’s own weight. The 500-ton figure names no source and no weight definition, so it corroborates the derivation and enters no calculation [Jacobs 2007, Thinking outside the tube, Wired]. The comparison against Liebeck also depends on the scaling law, and the ratio of 1.649 under the cube becomes 1.414 under the square of span. If the model was not weight-scaled with the precision assumed, the number moves and the comparison against Liebeck moves with it.

The relative density factor is now quantified, and it changes the answer. Taking the model’s condition at the field elevation of Rogers Dry Lake raises the implied full-scale weight from 854,875 pounds to 914,885, and taking it at the ceiling raises it to 1,157,634. No source consulted states the altitude at which the weight scaling was set, so 854,875 pounds is reported as a lower bound and every comparison drawn from it inherits that status.

The BWB-17 does not fit the same arithmetic. At 6 percent scale and 120 pounds [Liebeck 2004],

\[b_{\text{ref}} = \frac{17}{0.06} = 283\ \text{ft}, \qquad W_{\text{full}} = \frac{120}{0.06^{3}} = 555{,}556\ \text{lb}\]

The implied span agrees with the 280 feet of Liebeck’s second-generation design to within 1.2 percent, and the implied weight falls at 0.675 of that design’s 823,000 pounds, so either the BWB-17 answered to an earlier and lighter reference design or it was not weight-scaled to the vehicle described in the same paper. The record does not say which, and this article does not guess.

The wing area enters one section and rests on one programme document. The figure of 100.5 square feet is the correlation update’s, given in a presentation slide without the reference definition behind it [Vicroy 2011]. It enters only through the reference chord $c = S/b$ used to put the Reynolds numbers on an absolute footing, and the ratio of 40.35 does not depend on it at all, because the chord cancels between model and full scale. A reader who distrusts the area should discard the two absolute Reynolds figures and keep everything else, and the argument is built on the ratio for that reason.

The X-48C’s moment-arm loss is a sensitivity and not a measurement. No source consulted publishes the sweep of the outer trailing edge, the spanwise station of the C model’s twin tails, or the vertical surface areas of either aeroplane. The inboard station of 2.5 feet and the tail arm of order ten feet are assumptions, chosen to be plausible rather than derived, and the tabulated shifts move with them. What does not move is the sign, since the geometry admits no reading in which moving a surface inboard on an aft-swept planform lengthens its arm. The engine-count half of the same argument is exact, resting only on published thrusts and weights.

The claim that departure onset does not transfer from the flight vehicle is argued from the scaling relations and has not been measured. No source consulted states a full-scale departure angle of attack, so there is nothing to compare the model’s limiting angle against. A quantified Reynolds correction is not attempted, because it depends on the configuration’s separation behaviour, which is the unknown in question.

The claim is about the flight vehicle and must not be read as a claim about the programme. The programme ran higher-Reynolds tunnel tests as well and reports its free-flight method as correlating well with the observed flight limits [Vicroy 2011]. This article does not claim that the departure boundary was left to the model, because it was not.

The correlation update is a conference presentation rather than a technical report, so its findings arrive as summary lines without the data behind them [Vicroy 2011]. The stall angles of 24 and 14 degrees, the phrase about departure limiter assaults and the pitching-moment finding are quoted from slides, and a reader wanting the supporting curves will not find them there.

The X-48B’s own weight and thrust are stated two ways as well. The flight-test papers give a maximum weight of 525 pounds and 54 pounds of installed thrust an engine, while the fact sheet gives a gross weight of 523 pounds and three 50-pound engines of about 150 pounds combined, and the correlation update gives 523 pounds and a static thrust of 162 pounds [Risch et al 2009] [Regan 2008] [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Vicroy 2011]. At 523 pounds the implied full-scale weight is 851,618 pounds rather than 854,875, and at 50 pounds an engine the model’s thrust to weight is 0.2857 and its excess over the full-scale design 1.272 rather than 1.374. Each changes the size of a result, and neither reverses its sign.

The X-48C’s engine thrust is stated differently by two sources, 89 pounds in the fact sheet and 75 in the 2011 presentation [X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090] [Vicroy 2011]. Every engine-out figure for the C model moves with that choice, from 2.378 down to 2.004 against the full-scale trijet. The conclusion keeps its direction while its size shifts.

The full-scale thrust comparison uses Liebeck’s second-generation design and not the reference vehicle. The 0.2245 thrust-to-weight figure belongs to an 823,000-pound, 800-passenger commercial design [Liebeck 2004]. If the military reference vehicle is thrustier, the model’s 1.374 excess shrinks, and the engine-out conservatism shrinks with it.

The Source Base

The survey rests on 6,622 research records assembled from Crossref, the NASA Technical Reports Server and the Defense Technical Information Center, of which 977 are primaries, being 14.8 percent, and 974 of those are report primaries by the identifier rule set out under The Definition of Primary. Thirteen primaries are cited by identifier, three of them journal and conference papers that the identifier rule does not reach.

The programme’s own documents carry the argument. The ground-to-flight correlation update answers the article’s keystone question directly and reports the stall angles [Vicroy 2011]. The flight-test progress paper of the NASA and Boeing test team reports the first 39 flights and the uncommanded roll-offs [Risch et al 2009], the in-flight stability analysis reports the multisine excitation behind the envelope expansion [Regan 2008], and the post-stall command tracking paper reports the high angle of attack tests [Goldthorpe et al 2010].

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 it is a NASA Technical Reports Server url or carries a digital object identifier under the 10.21236 prefix, which Crossref registers for Defense Technical Information Center reports. The same report is therefore reachable through Crossref and through the Defense Technical Information Center under two different labels, and a rule keyed on where a record was found rather than on what it is would count such a report as secondary.

The definition excludes the conference papers of the American Institute of Aeronautics and Astronautics, abbreviated AIAA, that are among the most important sources here. Three of the article’s central documents are AIAA papers written by the people who flew the aeroplane, and no metric keyed on publisher will call them primary. 14.8 percent is a lower bound on how much of this survey is first-hand, and the thirteen identifier-cited primaries are the ones that actually carry the argument.

Thin Subjects

Four 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
the viscosity of air and its variation with temperature	kinematic viscosity, dynamic viscosity, sutherland, viscosity temperature, transport properties of air	1
the relative density factor and model mass scaling	relative density, mass scaling, inertia scaling, moment of inertia, ballasting, mass properties	4
engine-out on a two-engine against a three-engine layout	engine out, engine inoperative, asymmetric thrust, asymmetric power, critical engine, minimum control speed, engine failure, propulsion failure, thrust asymmetry, one engine, lateral trim, control power requirement	29
thrust to weight as a scaling invariant	thrust to weight, thrust loading, power loading, installed thrust, thrust required, excess thrust, climb performance, takeoff performance, thrust sizing	3

The viscosity of air is the clearest case, and its one record is Sutherland’s own paper. The word viscosity also names the viscosity of lubricating oils, canola oil, molten metals, protein solutions and supercooled sucrose, and the Saybolt conversion tables of the American Society for Testing and Materials, none of which is this subject. The viscosity of air as a function of temperature is not an under-served subject. It was settled by Sutherland in 1893 and has lived in tables ever since [Sutherland 1893] [U.S. Standard Atmosphere, 1976] [The NBS-NACA tables of thermal properties of gases].

This is the fourth kind of thin, which is a subject whose vocabulary does not discriminate, compounded by the third, which is a subject so settled it stopped generating papers. A bibliographic search is the wrong instrument for a tabulated physical constant, and the right one is the table itself, cited by its identifier.

Engine-out on a two-engine against a three-engine layout is a real but small literature about a configuration choice most transports do not face. That thrust to weight is invariant under Froude scaling is almost never published, because it follows from a force scaling as the cube and is dimensional analysis rather than a finding, so the article’s claim stands on the arithmetic.

What the Survey Admits

A record is admitted only when a person reading its title finds it on this article’s subject, which is the scaling, aerodynamics, flight dynamics, control, testing, noise, propulsion, design and structure of the aeroplane and of the free-flight model that stands for it, read against the argument rather than against a word. Many words this subject depends on also name something else, and a record that shares only such a word is excluded. Similitude and Froude scaling also belong to hydraulics, soil mechanics, glaciology, fire research and civil engineering. Remotely piloted aircraft are also a tool of agriculture, ecology, geology, medicine and journalism, and remotely operated machines also work on the ground and under water. Stability margin also describes electrical power grids, ground robots and nuclear reactors. Sizing also applies to clothing, transistors, numerical methods and military forces, and atmosphere also names weather, climate and atmospheric optics. Multisine excitation also measures batteries, living tissue and radio amplifiers, and the wind tunnel also tests cars, trains, bridges and buildings. Thrust also names a property of bearings, and rudder also names the rudder of a ship.

Spaceflight and weaponry share this subject’s aerodynamics and its test facilities but not its vehicle, so their records are excluded. Orbital mechanics and spacecraft control, launch and re-entry vehicles, hypersonic vehicles and the hypersonic and impulsive facilities that test them, missiles, projectiles, bombs and stores are excluded, except where a title’s subject is a method this article uses, such as free-flight testing, tunnel scale effects, control allocation or parameter identification, stated in its own terms. Aircraft subjects the argument does not use are excluded as well, among them airline and airport operations, air traffic and airspace integration, navigation, maintenance, tyres and ground handling, electrical and fuel systems, seats and crew equipment, accident statistics, teaching and military operations, and so are drones used as tools of another trade, with their path planning, swarming and machine vision. A record whose title and first author repeat another’s is one work deposited twice, a conference paper and its journal version or one report under two identifiers, and only the earliest deposit is counted. Correction, erratum, corrigendum and withdrawal notices, and the indexes and bibliographies printed in the back matter of books, are excluded too, because a survey counts research works and those are editorial events or parts of works.

Reviews of books, reference and definition entries and notices are not admitted, and a document deposited twice is admitted once. An authored encyclopedia article of more than two pages and a chapter of a textbook are research works and are kept. A publisher’s record of a whole conference volume, which lists a meeting’s papers and carries none of its own, and an abstract-journal listing are not admitted either.

Some records of doubtful relevance are kept. Multisine signal design and control allocation stated for any plant, structural similitude for scaled plates, shells and beams, the identification of missile, re-entry and parachute aerodynamics from flight data, free-flight testing in hypersonic facilities, the aerodynamics of wings at hypersonic speed, and the flight of birds and insects where the title is wing aerodynamics or a dynamically scaled model each share a method or a phenomenon with this subject, so each is kept and a reader may weigh it accordingly. No residual cluster remains, and every record sits in a cluster named for what its titles are.

Every research title has been read for relevance, so the off-topic share that remains is a matter of reading judgement. A reading of titles cannot show that a work is relevant in substance, so this is a statement about titles only.

Epistemic State

Historical Fact

The dates, the flight counts, the two configurations, the builder, the engine fits, the modification list for the X-48C and the block structure of the flight test programme are taken from NASA and Boeing publications and from the two AIAA papers. The uncommanded wing roll-off, the behaviour of lateral stick during it, the six and two occurrences in the two slat configurations and the successful pitch-over recoveries are reported in the flight-test progress paper. The stall angles of 24 and 14 degrees, the controllability three degrees beyond maximum lift, the six-block structure of phase one to flight 80, the description of the departure limiter assaults as highly successful, the plot of ground tests on axes of vehicle scale against chord Reynolds number, the finding that support interference on pitching moment was much larger than anticipated, the statement that the free-flight method correlated well with observed flight limits, and the list of comparisons never made are reported in the ground-to-flight correlation update. The departure boundary was not left to the flight vehicle alone. The programme ran a suite of ground tests spanning more than two decades of Reynolds number, up to about 70 million in the National Transonic Facility, as the correlation update records.

Verified by Independent Derivation

The scale factor of 0.085000 from the published span and reference span. The Froude ratio table. The time compression of 3.430 and the Reynolds penalty of 40.35. The comparison against the X-36 at 1.815 and 5.979. The ladder of three candidate vehicles and the factor of 2.247 in Reynolds number attributable to the X-48A cancellation. The implied full-scale weight of 854,875 pounds and its ratios against Liebeck’s design brought to the same span, 1.649 under the cube of span and 1.414 under its square, with 1.765 and 1.513 on the field-elevation reading and 2.234 and 1.915 at the ceiling. The scaled weights of 518,274 and 604,653 pounds. The fractions of 0.855, 0.915 and 1.158 that the three implied weights form of 1,000,000 pounds. The thrust-to-weight figures of 0.3086 and 0.2245 and their ratio of 1.374. The asymmetric thrust fractions of 0.10286, 0.17800 and 0.07485 and the ratios of 1.374, 2.378 and 1.731 that follow. The absolute Reynolds numbers of $6.24 \times 10^6$ and $2.52 \times 10^8$ at the stated reference chord. The kinematic viscosity ratio of 1.281 between 10,000 feet and sea level on the standard atmosphere, and the effective penalty of 51.7 that follows. The implied full-scale weights of 914,885 and 1,157,634 pounds at the two non-unity readings of the relative density factor. The full-scale equivalent speed of 404.7 knots. The BWB-17’s implied reference span of 283 feet and weight of 555,556 pounds, within 1.2 percent of the 280-foot span and at 0.675 of the 823,000-pound weight of Liebeck’s second-generation design.

Analysis

The division of the flight results into Froude-governed conclusions that transfer and Reynolds-governed conclusions that do not. The identification of the disagreement between Liebeck’s stated stall progression and the observed roll-off as the disagreement the scale factor predicts. The reading of the engine-out test as conservative because the model is over-thrusted. The geometric argument that moving a vertical surface inboard on a swept planform shortens its moment arm, and the tabulated sensitivity of that shift to an assumed sweep angle. The reading of the X-48C as doubly penalised on its weakest axis, by engine count exactly and by moment arm approximately. The placing of the article’s criticism on how the flight result is repeated rather than on how it was obtained.

Inference

That the reference vehicle is heavy for its span, inferred from the implied weight being 1.414 to 1.649 times a passenger design brought to the same span. That it is the heavy-lift military aeroplane for refuelling and cargo that Boeing described, consistent with that excess, with the Air Force’s stated interest and with the magazine’s figure of 500 tons, though the scale relations do not show how much of the excess the military role explains. That bracketing the leading edge with two slat configurations hedges the Reynolds uncertainty, a reading of the test matrix and not a stated rationale.

What the Record Does Not Settle

The reference vehicle’s actual weight, which no technical source consulted states and one magazine gives as a round 500 tons. The reference definition behind the correlation update’s wing area. The positions of the vertical surfaces on either aeroplane, and the sweep of the outer trailing edge. The full-scale departure angle of attack. Whether the BWB-17’s weight answers to the design published alongside it. Whether the X-48C’s noise objective was met, an acoustic result this article does not have. Which of the two published thrust ratings the X-48C actually flew with, 75 pounds an engine or 89, on which every engine-out figure for that aeroplane depends. What the aeroplane does past the departure boundary, which the programme itself lists as having no flight comparison at all.

Out of Scope

The acoustic measurements and the shielding result of the X-48C, which need a noise dataset this article does not have. The structural design of the non-circular pressure vessel, the configuration’s hardest problem but outside flight dynamics. The economics of the blended wing body against the tube and wing. The later Boeing and NASA transonic truss-braced and blended configurations that followed the X-48. The military airlift requirement that motivated Air Force interest.

Conclusion

The X-48 is the aeroplane in this series whose most consequential property is its size. It flew 122 times, it was controllable throughout the low-speed envelope, it departed in uncommanded wing roll-offs at a limiting angle of attack, and it recovered every time [X-48 Research, All Good Things Must Come to an End, NASA] [Risch et al 2009]. All four of those statements are true of a 20.4-foot aeroplane, and only three of them are evidence about a 240-foot one.

The departure boundary does not carry from the flight vehicle, and a reader wants it most. A free-flight model buys dynamic fidelity by surrendering Reynolds number, and at 8.5 percent the surrender is a factor of 40.35. That factor governs separation onset, and the most quoted single result of the flight programme is a separation phenomenon.

From the flight vehicle is the necessary qualification, and the campaign record supplies it. It flew both leading-edge configurations, which bracket the behaviour the scale factor makes least certain, and it plotted its ground tests on axes of scale against Reynolds number, up to about 70 million in the National Transonic Facility, short of the full-scale region the plot marks [Vicroy 2011]. The Reynolds-governed half was approached in the tunnels rather than assumed away. The campaign used both kinds of instrument, one that flies and one that reaches Reynolds number.

The disagreement this article began with survives that. The design paper says the outer wing keeps flying into the stall and the ailerons stay effective [Liebeck 2004]. The flight report says the aeroplane rolls off uncommanded and that roll input makes it worse [Risch et al 2009]. No amount of flying the model resolves that, and the programme’s list of what it could not compare includes post-departure behaviour [Vicroy 2011].

What the X-48 proved is that a control system can hold a large tailless transport at low speed and recover it from its own edge, three and a half times faster than the aeroplane will have to. In 2000 that was the open question and it is no longer.

The most useful thing in the record is not a result but a lesson about instruments. Asked where its ground-to-flight comparisons were poor, the programme does not name the stall or the scale factor. It names first the support that held the model in the tunnel [Vicroy 2011]. A campaign that spent nearly six years and 122 flights worrying about Reynolds number was caught out by the supports that held its tunnel models, and the lesson is worth more to the next programme than any number in this article.

References

Books

• Anderson, Aircraft performance and design
• Etkin and Reid, Dynamics of flight
• Hoerner and Borst, Fluid-dynamic lift
• McCormick, Aerodynamics, aeronautics and flight mechanics
• Nicolai and Carichner, Fundamentals of aircraft and airship design
• Raymer, Aircraft design, a conceptual approach
• Schlichting and Gersten, Boundary layer theory
• Torenbeek, Synthesis of subsonic airplane design
• Wooldridge, Winged wonders, the story of the flying wings

Reference

• Blended wing body
• Boeing C-17 Globemaster III
• Boeing flies X-48C blended wing body research aircraft
• Boeing Phantom Works to lead research on X-48B blended wing body concept
• Boeing X-48
• Cranfield Aerospace Solutions
• Jacobs 2007, Thinking outside the tube, Wired
• Northrop Grumman B-2 Spirit
• Parsch, Boeing X-48, Directory of U.S. Military Rockets and Missiles
• Rogers Dry Lake
• Second X-48B modified into X-48C configuration, NASA Dryden
• X-36 Tailless Fighter Agility Research Aircraft, NASA
• X-48 Blended Wing Body, GlobalSecurity
• X-48 Hybrid/Blended Wing Body, NASA Dryden Fact Sheet FS-090
• X-48 Research, All Good Things Must Come to an End, NASA

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• X-Planes: North American X-15
• X-Planes: Northrop Grumman X-47
• X-Planes: Northrop X-21
• X-Planes: Northrop X-4 Bantam
• X-Planes: Orbital Sciences X-34
• X-Planes: Orbital Sciences X-42
• X-Planes: Osprey X-28 Sea Skimmer
• X-Planes: Rockwell X-30 and the National Aero-Space Plane
• X-Planes: Rockwell-MBB X-31
• X-Planes: Ryan X-13 Vertijet
• X-Planes: Scaled Composites X-38
• X-Planes: Schweizer X-26 Frigate
• X-Planes: X-39, Reserved but Never Assigned
• X-Planes: X-41 Common Aero Vehicle
• X-Planes: X-44, One Designation and Two Aircraft

Research

• A Potential Flow Model 1976
• A Preliminary Investigation of 1976
• A Properties of Standard 2006
• A Review of Core 1975
• A Spreadsheet Tool for 2018
• A Standard Atmosphere 2022
• A Study on Prevention 2005
• A vectored-engine-over-wing propulsive-lift concept 1976
• A. et al 2018
• Aarnes and White 1975
• Aarnes and White 1975
• Aarons et al 2011
• Abate and Klomfass 2005
• Abbott et al 1982
• Abdallah 2018
• Abdallah et al 2013
• Abdallah et al 2014
• Abdel-Fattah and Link 1992
• Abdelgalil and Taha 2023
• Abdul Sathar Eqbal et al 2018
• Abdullahi et al 2026
• Abdulwahab and Chen 2008
• Abel and Newsom 1981
• Abele et al 1973
• Abeyratne 2016
• Abeyratne 2019
• Abnous et al 2017
• Abnous et al 2017
• Abou Khalil
• Abraham 1970
• Abraham and Costello 2009
• Abrams and Weinstein 1974
• Abramson 1975
• Abramson 1977
• Abrishami and Gong 2020
• Abumeri and Chamis 1996
• Abzalilov 2005
• Acher et al 2021
• Acheson and Gregory
• Acheson et al
• Acheson et al
• Acoustic Characteristics of a 1976
• Acoustic Investigation of the 1975
• Adamo 2023
• Adams and Rubin 1958
• Adamson et al 1978
• Addington 2000
• Addington and Myatt 2000
• Addington and Myatt 2000
• Adegbindin et al 2016
• Adelgren et al 2004
• Adhikari and Wei 2026
• Adler 1979
• Adler and Martins 2023
• Adolph 1981
• Adrian and Balachandar 2001
• Advanced Aircraft Control 2026
• Advanced Ducted Propulsor In-Flight
• Advanced Fuel Research Inc East Hartford Ct 1957
• AERO Dynamic Shape of 2014
• Aeroacoustics Jet Noise, Combustion 1976
• Aeroacoustics STOL Noise Airframe 1976
• Aerodynamic Control Forces and 2001
• Aerodynamic design of low-speed 1986
• Aerodynamic Design Wing 1969
• Aerodynamic Interference 2007
• Aerodynamic Interference 2018
• Aerodynamic Performance 2012
• Aerodynamic Performance of Swayasa 2025
• Aerodynamics 2024
• Aerodynamics and the 2016
• Aerodynamics of arbitrary wing 1976
• Aerodynamics of Wing-Body Combinations 2010
• Aeroelasticity Problems in Compressible 2010
• Aerospace - Flight Control
• Aerospace - Flight Control
• Aerospace - Vehicle Management
• Aerospace Active Inceptor Systems
• Afjeh and Reed 2003
• Agarwal 2004
• Agarwal and Dowling 2005
• Agarwal and Dowling 2007
• Agenbag et al 2009
• Agrawal et al 2024
• Agrawal et al 2025
• Ahad and Graham 2007
• Ahlefeldt 2017
• Ahlefeldt and Quest 2014
• Ahmad and Li 2022
• Ahmad et al 2008
• Ahmad et al 2018
• Ahmadi et al 2012
• Ahn et al 2017
• Ahtye and Kojima 1976
• Ahuja et al 2017
• Ahuja et al 2025
• Ahuja et al 2026
• Aidala 1985
• Air Force Flight Test Center Edwards Afb Ca 1970
• Air Force Flight Test Center Edwards Afb Ca 1974
• Air Force Flight Test Center Edwards Afb Ca 1974
• Air Force Flight Test Center Edwards Afb Ca 2002
• Air Force Test Pilot School Edwards Afb Ca 1962
• Air Force Test Pilot School Edwards Afb Ca 1962
• Air Force Test Pilot School Edwards Afb Ca 1962
• Air Force Test Pilot School Edwards Afb Ca 1967
• Air Force Test Pilot School Edwards Afb Ca 1967
• Air Force Test Pilot School Edwards Afb Ca 1979
• Air Force Test Pilot School Edwards Afb Ca 1981
• Air Force Test Pilot School Edwards Afb Ca 1987
• Air Force Test Pilot School Edwards Afb Ca 1988
• Air Force Test Pilot School Edwards Afb Ca 1988
• Air Force Test Pilot School Edwards Afb Ca 1988
• Air Force Test Pilot School Edwards Afb Ca 1988
• Air Force Test Pilot School Edwards Afb Ca 1988
• Air Force Test Pilot School Edwards Afb Ca 1989
• Air Force Test Pilot School Edwards Afb Ca 1990
• Air Force Test Pilot School Edwards Afb Ca 1990
• Air Force Test Pilot School Edwards Afb Ca 1990
• Air Force Test Pilot School Edwards Afb Ca 1990
• Air Force Test Pilot School Edwards Afb Ca 1990
• Air Force Test Pilot School Edwards Afb Ca 1991
• Air Force Test Pilot School Edwards Afb Ca 1991
• Air Force Test Pilot School Edwards Afb Ca 1991
• Air Force Test Pilot School Edwards Afb Ca 1992
• Air Force Test Pilot School Edwards Afb Ca 1992
• Air Force Test Pilot School Edwards Afb Ca 1993
• Air Proving Ground Center Eglin Afb Fl 1954
• Air Proving Ground Center Eglin Afb Fl 1955
• Aircraft and Flight Test 2021
• Aircraft Case Studies 2026
• Aircraft Characteristics 2022
• Aircraft Classification, Statistics, and 2010
• Aircraft Components and Subsystems 2011
• Aircraft Conceptual Design 2012
• Aircraft Control 2016
• Aircraft Cruise in Steady 2011
• Aircraft Cruise in Steady 2011
• Aircraft Design A Conceptual 2024
• Aircraft Design Optimization 2013
• Aircraft Dynamic Response Numerical 2014
• Aircraft Dynamic Stability 2003
• Aircraft Dynamic Stability 2014
• Aircraft Dynamic Stability 2024
• Aircraft Engine Controls Design 2012
• Aircraft Engine Controls Design 2017
• Aircraft Engine Efficiency and 2018
• Aircraft Equations of Motion 2003
• Aircraft Equations of Motion 2014
• Aircraft Equations of Motion 2022
• Aircraft Far-Field Aerodynamic Noise 1976
• Aircraft Flight Control 2014
• Aircraft Flight Control Actuation
• Aircraft Flight Control Systems
• Aircraft lateral-directional handling qualities 2011
• Aircraft longitudinal handling qualities 2011
• Aircraft Maneuvers and Flight 2011
• Aircraft Maneuvers and Flight 2011
• Aircraft Mechanics 2026
• Aircraft Model 2025
• Aircraft Models 2012
• Aircraft moments of inertia 1996
• Aircraft Noise Airframe 2022
• Aircraft Noise Flight Operations 2022
• Aircraft Noise Flight Trajectories 2012
• Aircraft Noise Noise Sources 2012
• Aircraft noise prediction 1989
• Aircraft Noise Propagation 2012
• Aircraft noise sources 1989
• Aircraft Operating Envelope 2010
• Aircraft Performance 2003
• Aircraft Performance 2014
• Aircraft Performance 2026
• Aircraft Range and Endurance 2011
• Aircraft Range and Endurance 2011
• Aircraft Simulation Model 2022
• Aircraft Sizing, Engine Matching 2010
• Aircraft Stability and Control 2003
• Aircraft Stability and Control 2014
• Aircraft Stability and Control 2022
• Aircraft Stability and Control 2024
• Aircraft Stability and Control 2026
• Aircraft Stability Characteristics in 2021
• Aircraft Stability Derivatives 2002
• Aircraft Static Stability 2003
• Aircraft Static Stability 2014
• Aircraft Static Stability 2024
• Aircraft Steady Gliding Longitudinal 2011
• Aircraft Steady Gliding Longitudinal 2011
• Aircraft Steady Level Turning 2011
• Aircraft Steady Level Turning 2011
• Aircraft Steady Longitudinal Flight 2011
• Aircraft Steady Longitudinal Flight 2011
• Aircraft Steady Turning Flight 2011
• Aircraft Steady Turning Flight 2011
• Aircraft Weight and Center 2010
• Aircraft Weight Distribution 2012
• Aircraft Wing Rock in 2010
• Aircraft/Engine System Constraint Analysis 2018
• Aircraft/Engine System Mission Analysis 2018
• Airfoil static-pressure thrust 1990
• Airframe noise radiation from 1993
• Airil
• Airplane Spin Testing 2003
• Airspeed Vs Flight Path 2003
• Ajaj et al 2013
• Akaryildiz et al 2024
• Akatsuka 2024
• Akatsuka et al 2022
• Akatsuka et al 2025
• Akram et al 2020
• Aksteter et al 1994
• Aksu 2014
• Al Aian et al 2014
• Al Tahtawi and Yusuf 2019
• Al-Jaburi et al 2019
• Al-Shehabi and Newman 2002
• Alag and Duke 1985
• Alag and Kaufman 1974
• Alam et al 2022
• Alatorre et al 2023
• Alauzet et al 2026
• Alaverdi and Paris 2001
• Alazard 2001
• Albisser
• Albrecht et al 2023
• Ale Isaac Khoueini
• Aleisa et al 2023
• Alexander 1970
• Alexander 1979
• Alexander 1991
• Alexander and Griffin 1974
• Alexander et al 1973
• Alexander et al 1975
• Alford and Knarr 1999
• Algozino et al 2015
• Alhosseinihamedani et al 2019
• Ali and Al-Shamma 2026
• Ali and Eladl 2002
• Ali et al 2011
• Ali et al 2012
• Ali et al 2016
• Ali et al 2023
• Ali et al 2024
• Ali et al 2025
• Ali et al 2025
• Ali et al 2025
• Alipour et al 2022
• Allan et al 2003
• Allen and Townsend 1985
• Allen et al 2015
• Alley et al 2007
• Almanza et al 1994
• Almosnino 2016
• Almuina Pica et al 2022
• Alscher et al 1966
• Alston 1939
• Altman 2015
• Altman 2019
• Altmann 2011
• Altoscan Co Landsdowne Pa 1957
• Altunkaya et al 2024
• Alwi and Edwards 2007
• Alwi and Edwards 2009
• Aly and Aly 1997
• Alyanak and Pendleton 2017
• Amann 1987
• Amato et al 2022
• Amick et al 1955
• Amiet 1975
• Amin and Das 2013
• Ammar and Trépanier 2014
• Ammar et al 2017
• An et al 2018
• An evaluation of sailplane 1974
• An Experimental Investigation of 1976
• An Experimental Study of 1976
• An Experimental Study of 1976
• Analysis of Gust-Response Flight-Test 1988
• Ananda and Selig 2016
• Ananda et al 2017
• Andersen et al 1996
• Anderson 1960
• Anderson 1968
• Anderson 1970
• Anderson 1984
• Anderson 1990
• Anderson and Averett 1972
• Anderson and Vincent 1985
• Ando et al 2017
• Andreu Angulo and Ansell 2018
• Andrew 1981
• Anex 1990
• Anex and Rock 1985
• Ang and Ng 2026
• Angelino et al 2019
• Angelucci 1971
• Angle of Attack Indicator 1960
• Anipko et al 2020
• Antonakis and Biannic 2024
• Antoniou et al 2025
• Anwar 2025
• Anyoji et al 2010
• Aono et al 2018
• Aoyagi et al 1972
• Appelbaum et al 2018
• APPENDICES A. Stability Derivatives 1990
• Appendix A Relevant flight 2011
• Appendix A Standard Atmosphere 2021
• Appendix A. The Standard 2011
• Appendix B Properties of 2003
• Appendix E Standard Atmosphere 1979
• Appendix E Standard atmosphere 2004
• Appendix G Development of 2003
• Appendix H Aerodynamics of 2010
• Appendix H Stability Characteristics 2003
• Application of dynamic flight
• Approximations for the thermodynamic and transport properties of high-temperature air
• Ardema 2003
• Arena and Nelson 1989
• Arena and Nelson 1991
• Arena et al 2021
• Arent and Falatko 1992
• Ariff et al 2015
• Arko and McQuilling 2012
• Armstrong 1977
• Army Aviation Board Fort Rucker Al 1957
• Army Aviation Board Fort Rucker Al 1964
• Army Scientific Advisory Panel Washington Dc 1977
• Army Service Forces Washington Dc 1940
• Army War Coll Carlisle Barracks Pa 1952
• Arnav Ahlawat 2026
• Arney et al 1964
• Arntz and Atinault 2015
• Arntzen 2012
• Arthur et al 2023
• Arunvinthan et al 2024
• Arévalo Nogales 2020
• Asada and Kawai 2018
• Asada and Kawai 2026
• Asaro and Vos 2025
• Asaro et al 2025
• Ascani 1974
• Aschenbeck 1964
• Aschwanden et al 2012
• Ashburn et al 1970
• Asher et al 1957
• Ashkenas 1965
• Ashkenas 1965
• Ashley 1967
• Ashraf and Van Kampen 2020
• Ashworth et al 1986
• Asmatulu et al 2009
• Asselin 2021
• Asymptotic methods for the 1991
• Atay et al 2021
• Atef and El Baz 2023
• Athkuri and Nived 2026
• Atias and Weihs 1983
• Atmaca et al 2026
• Atta and Nayfeh 1978
• Attar and Gordnier 2008
• Attar et al 2008
• Aubeelack
• Aubeelack et al 2023
• Aujogue
• Auman and Newby 2003
• Aume et al 1976
• Ausserer and Harmon 2012
• Autenrieb 2025
• Automatic flight control system 2000
• Autry and Victorazzo 2019
• Avanzini and Minisci 2010
• Avci et al 2026
• Axelson 1975
• Aydın et al 2026
• Ayers 1982
• Ayok 2026
• B-34. U. S. Standard 1963
• Babčan and Janovec 2021
• Bach 1980
• Bach and Parks 1987
• Bach and Wingrove 1983
• Bachelder and Aponso 2020
• Bachelder and Aponso 2020
• Bachelder and Klyde 2003
• Bachelder et al 2023
• Bachmaier and Anderson 2021
• Back-Up Flight Control System 1983
• Bacon and Roskman 1995
• Badia et al 2024
• Badole et al 2022
• Baeder et al 2003
• Baer 2014
• Bagby 1963
• Bagdatli et al 2019
• Baggi et al 2020
• Baggi et al 2022
• Baghiyan 2021
• Bagwill and Selberg 1996
• Bagy
• Bahl 2026
• Bahl et al 2020
• Bahr et al 2014
• Bai and Chen 2025
• Bai et al 2022
• Baier et al 2014
• Baigang 2024
• Baigang and Xuan 2022
• Bailey 1984
• Bainsla et al 2021
• Bajaj 2019
• Bak et al 2024
• Bakaul et al 2015
• Baker and Squire 1982
• Balachandran 2014
• Balakrishna and Niranjana 1987
• Balakumar 2009
• Balas et al 1996
• Balasubramanian et al 2026
• Balawi et al 2015
• Balcan et al 2026
• Baldwin 2007
• Balint and Balint 2015
• Balla and Vad 2022
• Ballard 1967
• Ballouz and Chang
• Balzer and Fasel 2010
• Ban et al 2018
• Banazadeh and Hajipouzadeh 2019
• Banazadeh et al 2007
• Bandyopadhyay and Gad-el-Hak 1994
• Banerjee 1984
• Banerjee 1988
• Banerjee 1988
• Banerjee et al 2026
• Bangert et al 1983
• Bannink and Houtman 1993
• Barbosa and Dezan 2013
• Barbosa and Dezan 2013
• Bare-Airframe Identification from Data 2006
• Bare-Airframe Identification from Data 2012
• Barker and Balas 1999
• Barlow 1929
• Barnard 2004
• Barnaud et al 2019
• Barnes 1965
• Barnhart 1989
• Barnwell et al 1986
• Barnwell et al 2003
• Baroff 1980
• Barrett 1952
• Barron 1967
• Barsh 1944
• Bartels 2013
• Barthelemy et al 1994
• Barton
• Barton and Mixson 1980
• Barwell 1973
• Basescu and Moore 2020
• Bashforth 1981
• Bashir et al 2023
• Basilio Chaves
• Bass 1986
• Bass et al 1993
• Bass et al 1995
• Bateman 1986
• Batill and Hoffman 1984
• Batill et al 1983
• Batther and Lee 2022
• Battipede et al 2004
• Battipede et al 2004
• Battipede et al 2005
• Bauch and Lair 1970
• Bauer 1979
• Bauer and Munson 1977
• Bauer et al 2009
• Bauer et al 2012
• Baumann and Gal-Or 1992
• Baumann and Waggoner 2018
• Baumgartner et al 1958
• Baumgartner et al 1979
• Bazile and Calderara 2012
• Bazill and Jenney 1970
• Bazin and Fields 2015
• Beamer
• Bean and Lee 1994
• Bean and Lee 1995
• Beatty et al 1977
• Beaufrere 1988
• Becht and Knight 1995
• Becker et al 2011
• Beckwith 1974
• Bedford and Lowenberg 2006
• Begin 1983
• Begnini et al 2018
• Beh et al 2018
• Beitler 1984
• Belisle et al 2010
• Belkharraz and Sobel 2000
• Belkharraz and Sobel 2001
• Bell 1974
• Bell Aerospace Co Buffalo Ny 1956
• Bellankimath and Chandar 2015
• Belligoli et al 2019
• Belligoli et al 2019
• Belsterling 1976
• Belyaev et al 2015
• Ben Asher and Raveh 2023
• Bendarkar et al 2013
• Bender et al 2010
• Bending of an Aircraft-Wing 2019
• Benek 1977
• Benito 1986
• Benjamin et al 2023
• Bennani and Looye 1998
• Bennett 1947
• Bennett and Abel 1981
• Bennett and Abel 1982
• Bennett et al 2017
• Bennington and Simpson 2004
• Benoit et al 2014
• Benosman et al 2007
• Benton and Visbal 2017
• Benton and Visbal 2018
• Benton and Visbal 2018
• Benton and Visbal 2019
• Benyamen and Keshmiri 2022
• Beppu et al 1966
• Berci and Torrigiani 2020
• Berdjag et al 2010
• Berens and Bissinger 1998
• Berge et al 1993
• Berger et al 2011
• Berman 1980
• Bernardini et al 2014
• Bernardini et al 2016
• Bernstein and Hamid 1995
• Berra et al 2017
• Berry 2000
• Berry and Chopra 2013
• Berry et al 1979
• Bertelrud 1979
• Bertelrud 1981
• Bertelrud 1998
• Bertelrud and Nordstrom 1983
• Bertelrud et al
• Bertelrud et al 1988
• Bertolino et al 2024
• Berton 2016
• Berton 2023
• Berton and Majjigi 2025
• Bertsch et al 2010
• Bertsch et al 2025
• Bever 1992
• Beyak et al 2024
• Beyers 1983
• Beyers 1991
• Beyers 1992
• Beyers 1995
• Beyers 2002
• Beyers et al 1997
• Bhat and Gall 1975
• Bhattarai et al 2026
• Bian et al 2018
• Bian et al 2019
• Biber and Mendoza 1994
• Bicego
• Bidwell 2005
• Bidwell and Mohler 1995
• Bigdeli and Monfared 2020
• Bigler 1986
• Bihrle 1970
• Bihrle 1993
• Bihrle and Billy 1980
• Bihrle and Meyer 1976
• Bihrle et al 1989
• Bil 1989
• Bilanin 1987
• Bilendo and Shouzhao 2018
• Bilger et al 1981
• Billingsley 1976
• Binbin et al 2022
• Bindolino et al 2010
• Binion 1969
• Binion 1970
• Binion 1971
• Binion 1974
• Binion 1975
• Binion and Lo 1972
• Binkley et al 2015
• Binwen Lu et al 2016
• Birch 2023
• Birch and Lee 2005
• Birckelbaw and Corliss 1992
• Birckelbaw and Corliss 1992
• Bird 1970
• Bird 1973
• Bischoff and Palmer 1982
• Bischoff and Palmer 1983
• Bishara et al 2018
• Bishop and Pearsons 1965
• Black 1956
• Black and Brownrigg 1966
• Black and Moorhouse 1979
• Blackwell 1978
• Blackwell et al 1981
• Blacodon 2005
• Blacodon 2007
• Blaesser and Frederick 2020
• Blair et al 2008
• Blake 2002
• Blake et al 2009
• Blandeau et al 2018
• Blank 1995
• Blasi and Core 2007
• Blech et al 2024
• Bleimeyer 1981
• Blick and Homer 1971
• Blight et al 2018
• Bliss 1980
• Block 1979
• Block 1981
• Bloomer 1979
• Bloy and Lea 1995
• Blue et al 2002
• Bodavula et al 2019
• Bodonyl 1994
• Bodson 2000
• Bodson 2001
• Boehler 1959
• Boeing flies blended wing 2008
• Boeing Phantom Works leading 2006
• Boeing Vertol Co Philadelphia Pa 1983
• Boelens 2009
• Boer and Van Hengst 1993
• Bogos 2020
• Bogue 1992
• Bohl and Hrynuk 2024
• Boiko et al 2024
• Boiko et al 2024
• Boisseau 1955
• Boland et al 1993
• Bolds 1961
• Bolds 1962
• Bolds-Moorehead et al 2015
• Bolsunovsky et al 2001
• Bombois et al 2021
• Bombois et al 2025
• Bon 2021
• Bond et al 2010
• Bonnema and Smith 1988
• Booker et al 2000
• Boothe et al 1974
• Borden 1930
• Borger 1981
• Borst 1978
• Bos 1999
• Boschetti et al 2004
• Boschetti et al 2020
• Boschetti et al 2022
• Bose et al 2022
• Boskovic and Mehra
• Boskovic and Mehra 1999
• Boskovic and Mehra 2000
• Boskovic et al
• Boskovic et al
• Boskovic et al 1998
• Bottasso and Montinari 2013
• Bouadi
• Boudreau 1976
• Boudreau 1977
• Boudreault 1983
• Boughou et al 2023
• Boukhebouz et al 2021
• Bounecer and Bahi 2018
• Bourdin et al 2007
• Bousman 1998
• Bousman 2003
• Boutilier and Yarusevych 2012
• Bovais et al 1992
• Bowden and Shockey 1970
• Bowditch 1986
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• Bowers 1980
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• Bowes 1978
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• Brandt and Bons 2023
• Brandt and Bons 2024
• Brandt et al 2011
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• Brandt et al 2022
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• Branson 1994
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• Braun 1958
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• Brendel and Mueller 1987
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• Brennan and McDaniel 1994
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• Brewer 2017
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• Britcher 1989
• Britcher and Landman 2024
• Britcher and Landman 2024
• Britcher and Landman 2024
• Britcher and Landman 2024
• Broadbent 1976
• Broderick
• Brodersen
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• Brodsky and Luby 2013
• Brody and Fagley 2024
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