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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Subsonic and supersonic wind tunnel study of low aspect ratio sweptback wing tailless fighter aircraft model/stability and control
Flight-determined stability & control derivatives of supersonic aircraft with low aspect ratio unswept wing & t-tail
Wind tunnel tests of wingless low aspect ratio folding control missile configurations
Aerodynamic characteristics of low-aspect-ratio wings at supersonic speeds
Wind tunnel tests on aspect ratio 2.17 delta wing model with midchord boundary layer control flaps
Longitudinal aerodynamic characteristics of 1/30 scale nuclear powered canard aircraft model having wing with aspect ratio 6.0
Effects of aspect ratio and canopy shape on longitudinal and lateral aerodynamic characteristics of parawings having 50 degree sweepback leading edges
Flight measured ground effect on low-aspect-ratio Ogee wing compared with wind tunnel results
Low speed wind tunnel testing of high aspect ratio variable sweep wing supersonic transport model for determining methods of reducing pitch-up tendency
Quasi-slender body theory for oscillating low aspect ratio wings and bodies of revolution in supersonic flow
Wind tunnel stability test of low aspect ratio delta winged model equipped with sharp-edged strakes
Influence of ground induced aerodynamic effects on landing maneuver of aircraft with low aspect ratio wings
Analyses of aspect ratio and curvature variations for axial flow compressor inlet stages under loading
Low speed static aerodynamic characteristics of three ram-air inflated low aspect ratio fabric wings
Interfiber distance and temperature effect on critical aspect ratio in composites
Interfiber distance and temperature effects on critical aspect ratio in fiber composites obtained from modified pull-out test
An investigation has been made of a complete airplane model having a wing with the quarter-chord line swept back 40 degrees, aspect ratio 2.50, and taper ratio 0.42 to determine its low-speed stability and control characteristics. The longitudinal stability investigation included stabilizer and tail-off tests with different wing dihedral angles (Gamma = 0 degrees and Gamma = -10 degrees) over an angle-of-attack range for the cruising and landing configurations and tests. with a high horizontal-tail location (Gamma = -10 degrees) for the cruising configuration. Tests were made of the wing alone and to determine the effect of wing end plates in pitch. Lateral stability characteristics were determined for the airplane with different geometric wing dihedrals, with end plates, and with several dorsal modifications. Tests were made with ailerons and spoilers to determine control characteristics.
Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.