NASA for Aerodynamics
A selection has been made of NASA documents related to the ESDU Aerodynamics Series. We are providing these to our users as a useful reference source.
These NASA documents have not been validated by ESDU but contribute to a comprehensive collection of design information and can be used along side ESDU methods for comparison and analysis to solve design problems. They also provide a possible resource in areas not currently covered by ESDU.
This Collection contains:
-
NASA-CR-120
Self-sealing structures for control of the meteoroid hazard to space vehicles -
NASA-CR-152-241
Estimation of tunnel blockage from wall pressure signatures: A review and data correlation -
NASA-CR-413
Linear aerodynamic loads on cone-cylinders at Mach numbers from 0.7 to 2.0 -
NASA-CR-1285
Potential structural materials and design concepts for light aircraft -
NASA-CR-1646
A design summary of stall characteristics of straight wing aircraft -
NASA-CR-1783
Full-scale wind tunnel tests of a low-wing, single-engine, light plane with positive and negative propeller thrust and up and down flap deflection -
NASA-CR-1843supp
Mathematical model for two-dimensional multicomponent airfoils in viscous flow -
NASA-CR-1843
Mathematical model for two-dimensional multicomponent airfoils in viscous flow -
NASA/CR-1999-209002
Advanced Turbofan Duct Liner Concepts -
NASA-CR-2214
Two-dimensional wind-tunnel tests of a NASA supercritical airfoil with various high-lift systems. Volume 1: Data analysis -
NASA-CR-2215
Two-dimensional wind-tunnel tests of a NASA supercritical airfoil with various high-lift systems. Volume 2: Test data -
NASA-CR-2299
Pressure recovery performance of conical diffusers at high subsonic Mach numbers -
NASA-CR-2334
Correlation of full-scale drag predictions with flight measurements on the C-141A aircraft : Phase 2: Wind tunnel tests, analysis, and prediction techniques. Volume 2: Wind tunnel test and basic data -
NASA-CR-2443
Development of a Fowler flap system for a high performance general aviation airfoil -
NASA-CR-2473
Effect of symmetrical vortex shedding on the longitudinal aerodynamic characteristics of wing-body-tail combinations -
NASA-CR-2538
Effectiveness of spoilers on the GA(W)-1 airfoil with a high performance Fowler flap -
NASA-CR-2682
Fluid mechanical model of the acoustic impedance of small orifices -
NASA-CR-2696
Reflection-plane tests of spoilers on an advanced technology wing with a large Fowler flap -
NASA-CR-2714
Landing gear and cavity noise prediction -
NASA-CR-2779
Finite state modeling of aeroelastic systems -
NASA-CR-2833
Force and pressure tests of the GA(W)-1 airfoil with a 20 aileron and pressure tests with a 30 Fowler flap -
NASA-CR-3081
Wind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoiler -
NASA-CR-3449
Calculation of vortex lift effect for cambered wings by the suction analogy -
NASA-CR-3515
A computer program for wing subsonic aerodynamic performance estimates including attainable thrust and vortex lift effects -
NASA-CR-3576
Study to determine the IFR operational profile and problems of the general aviation single pilot -
NASA-CR-3664
Development of aerodynamic prediction methods for irregular planform wings -
NASA-CR-3808
Numerical methods and a computer program for subsonic and supersonic aerodynamic design and analysis of wings with attainable thrust considerations -
NASA-CR-4653
Effects of cavity dimensions, boundary layer, and temperature on cavity noise with emphasis on benchmark data to validate computational aeroacoustic codes -
NASA-CR-4746
High-Lift Systems on Commercial Subsonic Airliners -
NASA-CR-61365
Results of a study of Mach number and Reynolds number effects on the crossflow drag characteristics of ogive cylinders and ogive-cylinder-frustum-cylinders at angles of attack to 30 degrees -
NASA-CR-96008
Aircraft stability and control data -
NASA-CR-98737
Wind tunnel investigations of vortex breakdown on slender sharp edged wings Final report -
NASA-CR-145627
Proceedings of the NASA, Industry, University, General Aviation Drag Reduction Workshop -
NASA-CR-152141
Prop-fan data support study -
NASA-CR-165768
Design and analysis of a fuel-efficient single-engine, turboprop-powered, business airplane -
NASA-CR-165843
Application of an aerodynamic analysis method including attainable thrust estimates to low speed leading-edge flap design for supersonic cruise vehicles -
NASA-CR-176615
Exploratory low-speed wind-tunnel study of concepts designed to improve aircraft stability and control at high angles of attack -
NASA-MEMO-1-16-59L
Semiempirical Procedure for Estimating Lift and Drag Characteristics of Propeller-Wing-Flap Configurations for Vertical-and Short-Take-Off-and-Landing Airplanes -
NASA-MEMO-4-1-59L
Effect of Horizontal-Tail Chord on the Calculated Subsonic Span Loads and Stability Derivatives of Isolated Unswept Tail Assemblies in Sideslip and Steady Roll -
NASA-MEMO-5-12-59A
Surface Pressure Distribution at Hypersonic Speeds for Blunt Delta Wings at Angle of Attack -
NASA-MEMO-5-16-59A
The Static and Dynamic Rotary Stability Derivatives at Subsonic Speeds of an Airplane Model Having Wing and Tail Surfaces Swept Back 45 degrees -
NASA-MEMO-5-20-59L
Low-Subsonic Measurements of the Static and Oscillatory Lateral Stability Derivatives of a Sweptback-Wing Airplane Configuration at Angles of Attack from -10 to 90 deg -
NASA-MEMO-6-5-50A
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of the Static and Dynamic Stability Derivatives of an Airplane Model with an Unswept Wing and a High Horizontal Tail -
NASA-MEMO-10-3-58A
Inclined Bodies of Various Cross Sections at Supersonic Speeds -
NASA-MEMO-12-1-58A
Estimation of Directional Stability Derivatives at Moderate Angles and Supersonic Speeds -
NASA-MEMO-12-2-58A
Estimation of Directional Stability Derivatives at Small Angles and Subsonic and Supersonic Speeds -
NASA-MEMO-12-21-58L
The Total-Pressure Recovery and Drag Characteristics of Several Auxiliary Inlets at Transonic Speeds -
NASA-PD-ED-1259
Acoustic Noise Requirement -
NASA-RP-1060
Subsonic aircraft: Evolution and the matching of size to performance -
NASA-RP-1145
Introduction to time series analysis -
NASA-RP-1258
Aeroacoustics of flight vehicles: Theory and practice. Volume 2: Noise control -
NASA-SP-347
Aerodynamic Analyses Requiring Advanced Computers, part 2 -
NASA-SP-3004
Tables for supersonic flow around right circular cones at zero angle of attack -
NASA-SP-3007
Tables for supersonic flow around right circular cones at small angle of attack -
NASA-SP-3070
Summary of transformation equations and equations of motion used in free flight and wind tunnel data reduction and analysis -
NASA-TM-4209
Three-dimensional cavity flow fields at subsonic and transonic speeds -
NASA-TM-4363
Measurements of fluctuating pressure in a rectangular cavity in transonic flow at high Reynolds numbers -
NASA-TM-4436
Characterization of cavity flow fields using pressure data obtained in the Langley 0.3-Meter Transonic Cryogenic Tunnel -
NASA-TM-4549
Effect of passive venting on static pressure distributions in cavities at subsonic and transonic speeds -
NASA-TM-4611
Measurements of store forces and moments and cavity pressures for a generic store in and near a box cavity at subsonic and transonic speeds -
NASA-TM-4741
Computer Program to Obtain Ordinates for NACA Airfoils -
NASA-TM-72863
Stability and control derivative estimates obtained from flight data for the Beech 99 aircraft -
NASA-TM-76710
Influence of the Reynolds number on normal forces of slender bodies of revolution -
NASA-TM-78533
Investigation of the asymmetric aerodynamic characteristics of cylindrical bodies of revolution with variations in nose geometry and rotational orientation at angles of attack to 58 degrees and Mach numbers to 2 -
NASA-TM-78650
Wind-tunnel results for an improved 21-percent-thick low-speed airfoil section -
NASA-TM-78709
NASA low- and medium-speed airfoil development -
NASA-TM-78813
Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from minus 4 deg to 60 deg -
NASA-TM-81912
Low-speed aerodynamic characteristics of a 14-percent-thick NASA phase 2 supercritical airfoil designed for a lift coefficient of 0.7 -
NASA-TM-85674
Aileron effectiveness for a subsonic transport model with a high-aspect-ratio supercritical wing -
NASA-TM-85760
Wind-tunnel investigation of an advanced general aviation canard configuration -
NASA-TM-87659
Supersonic axial-force characteristics of a rectangular-box cavity with various length-to-depth ratios in a flat plate -
NASA-TM-X-35
Effects of vertical-tail size and a ventral fin on the static lateral and directional stability derivatives of a 0.048-scale model of a horizontal-attitude VTOL airplane at transonic speeds -
NASA-TM-X-39
Dynamic Longitudinal and Directional Stability Derivatives for a 45 deg. Sweptback-Wing Airplane Model at Transonic Speeds -
NASA-TM-X-213
Investigation of the aerodynamic characteristics of a supersonic horizontal- attitude VTOL airplane model at Mach numbers of 1.57, 2.14, 2.54, and 2.87 -
NASA-TM-X-311
A wind-tunnel investigation of the aerodynamic characteristics of bodies of revolution at mach numbers of 2.37, 2.98, and 3.90 at angles of attack to 90 deg -
NASA-TM-X-1517
Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies -
NASA-TM-X-1658
Aerodynamic characteristics of bodies of revolution at Mach numbers from 1.50 to 2.86 and angles of attack to 180 deg -
NASA-TM-X-1785
Jet effects on boattail pressure drag of isolated ejector nozzles at Mach numbers from 0.60 to 1.47 -
NASA-TM-X-1931
Loss of forced cooling flow in the Plum Brook Reactor -
NASA-TM-X-1960
Jet effects on the boattail axial force of conical afterbodies at subsonic and transonic speeds -
NASA-TM-X-2163
Some transonic and supersonic dynamic stability characteristics of a variable-sweep-wing tactical fighter model -
NASA-TM-X-2284
Stability and control characteristics at Mach numbers 1.60 to 2.86 of a variable-sweep fighter configuration with supercritical airfoil sections -
NASA-TM-X-2313
Large-scale wind-tunnel tests of a propeller-driven deflected slipstream STOL model in ground effect -
NASA-TM-X-2555
Supersonic aerodynamic damping and oscillatory stability in pitch and yaw fro a model of a variable-sweep fighter airplane with twin vertical tails -
NASA-TM-X-2917
An investigation of several NACA 1 series axisymmetric inlets at Mach numbers from 0.4 to 1.29 -
NASA-TM-X-3078
Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage -
NASA-TM-X-3087
Lateral-directional stability characteristics of a wing-fuselage configuration at angles of attack up to 44 deg -
NASA-TM-X-3128
Experimental aerodynamic characteristics for a cylindrical body of revolution with various noses at angles of attack from 0 deg to 58 deg and Mach numbers from 0.6 to 2.0 -
NASA-TM-X-3160
Experimental and theoretical low speed aerodynamic characteristics of the NACA 65 sub 1-213, alpha equals 0.50, airfoil -
NASA-TM-X-3166
Low-speed wind-tunnel investigation of forward-located spoilers and trailing splines as trailing-vortex hazard-alleviation devices on an aspect-ratio-8 wing model -
NASA-TM-X-3222
Effect of entry-lip design on aerodynamics and acoustics of high throat Mach number inlets for the quiet, clean, short-haul experimental engine -
NASA-TM-X-3292
Measurements of farfield sound generation from a flow-excited cavity -
NASA-TM-X-3324
An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass flow ratios near 1.0 -
NASA-TM-X-3437
Side forces on a tangent ogive forebody with a fineness ratio of 3.5 at high angles of attack and Mach numbers from 0.1 to 0.7 -
NASA-TM-X-3438
Side forces on forebodies at high angles of attack and Mach numbers from 0.1 to 0.7: two tangent ogives, paraboloid and cone -
NASA-TM-X-56023
Drag reduction obtained by rounding vertical corners on a box-shaped ground vehicle -
NASA-TM-X-57779
Meeting on Ground Wind Load Problems in Relation to Launch Vehicles -
NASA-TM-X-62197
Wind tunnel investigation of a large-scale 25 deg swept-wing jet transport model with an external blowing triple-slotted flap -
NASA-TM-X-71903
A theoretical study of the acoustic impedance of orifices in the presence of a steady grazing flow -
NASA-TM-X-72078
Characteristics of Coupled Nongray Radiating Gas Flows with Ablation Product Effects About Blunt Bodies During Planetary Entries -
NASA-TM-X-72697
Low-speed aerodynamic characteristics of a 13-percent-thick airfoil section designed for general aviation applications -
NASA-TM-X-72843
Effects of thickness on the aerodynamic characteristics of an initial low-speed family of airfoils for general aviation applications -
NASA-TM-X-74018
Low-speed wind tunnel results for a modified 13-percent-thick airfoil -
NASA-TN-636
The estimation of the rate of change of yawing moment with sideslip -
NASA-TN-D-55
Wind-tunnel investigation of longitudinal aerodynamic characteristics of three propeller-driven VTOL configurations in the transition speed range, including effects of ground proximity -
NASA-TN-D-103
Investigation of double slotted flaps on a swept-wing transport model -
NASA-TN-D-209
The rolling moment due to sideslip of swept wings at subsonic and transonic speeds -
NASA-TN-D-217
Low-speed investigation of static longitudinal and lateral stability characteristics of an airplane configuration with a highly tapered wing and with several body and tail arrangements -
NASA-TN-D-232
Experimental determination of the effects of frequency and amplitude of oscillation on the roll-stability derivatives for a 60 degree delta-wing airplane model -
NASA-TN-D-318
A wind-tunnel investigation of three propellers through an angle-of-attack range from 0 deg to 85 deg -
NASA-TN-D-363
Investigation of the aerodynamic characteristics of a combination jet-flap and deflected-slipstream configuration at zero and low forward speeds -
NASA-TN-D-455
Effect of Reynolds Number on the Force and Pressure Distribution Characteristics of a Two-Dimensional Lifting Circular Cylinder -
NASA-TN-D-523
Investigation of the flow in a rectangular cavity in a flat plate at a mach number of 3.55 -
NASA-TN-D-926
Aerodynamic Characteristics of Low-Aspect-Ratio Wings in Close Proximity to the Ground -
NASA-TN-D-970
Effect of Ground Proximity on the Aerodynamic Characteristics of Aspect-Ratio-1 Airfoils With and Without End Plates -
NASA-TN-D-1024
Measured surface defects on typical transonic airplanes and analysis of their drag contribution -
NASA-TN-D-1394
A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes -
NASA-TN-D-1586
Aerodynamic data on large semispan tilting wing with 0.6-diameter chord, single slotted flap, and single propeller rotating up at tip -
NASA-TN-D-1620
Effect of cross-section shape on the aerodynamic characteristics of bodies at mach numbers from 2.50 to 4.63 -
NASA-TN-D-2042
Effect of afterbody geometry and sting diameter on the aerodynamic characteristics of slender bodies at mach numbers from 1.57 to 2.86 -
NASA-TN-D-2180
Aerodynamic data on a large semispan tilting wing with 0.6-diameter chord, fowler flap, and single propeller rotating up at tip -
NASA-TN-D-2201
Longitudinal aerodynamic characteristics of blunted cones at mach numbers of 3.5, 4.2 and 6.0 -
NASA-TN-D-2339
Correlation graphs for supersonic flow around right circular cones at zero yaw in air as a perfect gas -
NASA-TN-D-2350
Afterbody pressures on two-dimensional boattailed bodies having turbulent boundary layers at mach 5.98 -
NASA-TN-D-2373
A review of the stall characteristics of swept wings -
NASA-TN-D-2412
Aerodynamic data on large semispan tilting wing with 0.6-diameter chord, single-slotted flap, and single propeller rotating down at tip -
NASA-TN-D-2824
Large-scale wind-tunnel investigation of the low-speed aerodynamic characteristics of a supersonic transport model having variable- sweep wings -
NASA-TN-D-2970
A description of numerical methods and computer programs for two-dimensional and axisymmetric supersonic flow over blunt-nosed and flared bodies -
NASA-TN-D-3021
Flight-determined low-speed lift and drag characteristics of the lightweight m2-f1 lift- ing body -
NASA-TN-D-3088
Aerodynamic characteristics of spherically blunted cones at Mach numbers from 0.5 to 5.0 -
NASA-TN-D-3159
Aerodynamic damping and oscillatory stability in pitch for a model of a typical subsonic jet-transport airplane -
NASA-TN-D-3375
Aerodynamic data on a large semispan tilting wing with 0.5-diameter chord, double-slotted flap, and both left-hand and right-hand rotation of a single propeller -
NASA-TN-D-3437
Investigation of a semispan tilt-wing VTOL MODEL to determine ground effect on full-span flaps used for yaw control in hovering -
NASA-TN-D-3438
Longitudinal stability and control characteristics of a powered model of a twin-propeller deflected-slipstream STOL AIRPLANE configuration -
NASA-TN-D-3583
Ground effects related to landing of airplanes with low-aspect-ratio wings -
NASA-TN-D-3591
Static and dynamic longitudinal stability derivatives of a powered 1/9-scale model of a tilt-wing V/STOL transport -
NASA-TN-D-3767
A concept of the vortex lift of sharp-edge delta wings based on a leading-edge-suction analogy -
NASA-TN-D-3781
Effects of aft-fuselage-mounted nacelles on the subsonic longitudinal aerodynamic characteristics of a twin-turbojet airplane -
NASA-TN-D-3797
Large-scale wind tunnel tests of a subsonic transport with AFT engine nacelles and high tail -
NASA-TN-D-3845
Rolling stability derivatives of a variable- sweep tactical fighter model at subsonic and transonic speeds -
NASA-TN-D-4076
Static stability characteristics at Mach numbers from 1.90 to 4.63 of a 76 deg swept arrow wing model with variations in horizontal-tail height, wing height, and dihedral -
NASA-TN-D-4083
Investigation over moving ground plane of a transport airplane model using blowing over flaps for boundary-layer control -
NASA-TN-D-4448
Large-scale wind-tunnel tests of a deflected slipstream STOL model with wings of various aspect ratios -
NASA-TN-D-4563
Calculation of axisymmetric supersonic flow past blunt bodies with sonic corners, including a program description and listing -
NASA-TN-D-4664
Wind-tunnel study to explore the use of slot spoilers to modulate the flap-induced lift of a wing -
NASA-TN-D-4719
Supersonic aerodynamics of large-angle cones -
NASA-TN-D-4792
Heat transfer and pressure distributions on spherically blunted 25 deg half-angle cone at Mach 8 and angles of attack up to 90 deg -
NASA-TN-D-4821
Effect on base drag of recessing the bases of conical afterbodies at subsonic and transonic speeds -
NASA-TN-D-4856
Aerodynamic characteristics of twin propeller deflected slipstream STOL airplane model with boundary layer control on inverted V-tail -
NASA-TN-D-4891
Prediction of lift and drag for slender sharp-edge delta wings in ground proximity -
NASA-TN-D-4928
Wind-tunnel investigation of a large jet transport model equipped with an external-flow jet flap -
NASA-TN-D-4929
Theory for computing span loads and stability derivatives due to sideslip, yawing, and rolling for wings in subsonic compressible flow -
NASA-TN-D-4983
Full-scale wind-tunnel investigation of static longtudinal and lateral characteristics of a light twin-engine airplane -
NASA-TN-D-5054
Experimental pressure distributions on a 120 deg cone at Mach numbers from 2.96 to 4.63 and angles of attack from 0 deg to 20 deg -
NASA-TN-D-5102
Large-scale tests of an airplane model with a double-delta wing, including longitudinal and lateral characteristics and ground effects -
NASA-TN-D-5153
The use of pilot rating in the evaluation of aircraft handling qualities -
NASA-TN-D-5204
Pressure distributions on 140 deg, 160 deg, and 180 deg cones at Mach numbers from 2.30 to 4.63 and angles of attack from 0 deg to 20 deg -
NASA-TN-D-5361
Analysis of lateral directional stability characteristics of a twin jet fighter airplane at high angles of attack -
NASA-TN-D-5364
Wind-tunnel investigation of a STOL aircraft configuration equipped with an external-flow jet flap -
NASA-TN-D-5392
Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 deg to 15 deg -
NASA-TN-D-5408
Static and dynamic stability derivatives of a model of a jet transport equipped with external-flow jet-augmented flaps -
NASA-TN-D-5662
Effects of ground proximity on the longitudinal aerodynamic characteristics of an unswept aspect-ratio-10 wing -
NASA-TN-D-5700
Full-scale wind-tunnel investigation of the static longitudinal and lateral characteristics of a light single-engine airplane -
NASA-TN-D-5805
Buffet and static aerodynamic characteristics of a systematic series of wings determined from a subsonic wind-tunnel study -
NASA-TN-D-5857
Full-scale wind-tunnel investigation of the static longitudinal and lateral characteristics of a light single-engine low- wing airplane -
NASA-TN-D-5971
Longitudinal aerodynamic characteristics of a twin-turbofan subsonic transport with nacelles mounted under the wings -
NASA-TN-D-6053
Flight evaluation of ground effect on several low-aspect-ratio airplanes -
NASA-TN-D-6058
Wind-tunnel investigation of a jet transport airplane configuration with high thrust-weight ratio and an external-flow jet flap -
NASA-TN-D-6091
Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 deg to 110 deg -
NASA-TN-D-6222
Effect of engine position and high-lift devices on aerodynamic characteristics of an external-flow jet-flap STOL model -
NASA-TN-D-6238
A wind tunnel investigation of static longitudinal and lateral characteristics of a full-scale mockup of a light twin engine airplane -
NASA-TN-D-6243
Charts for predicting the subsonic vortex-lift characteristics of arrow, delta, and diamond wings -
NASA-TN-D-6263
Lift and drag characteristics of the HL-10 lifting body during subsonic gliding flight -
NASA-TN-D-6283
A time-dependent method for calculating supersonic angle-of-attack flow about axisymmetric blunt bodies with sharp shoulders and smooth nonaxisymmetric blunt bodies -
NASA-TN-D-6344
Experimental and analytical investigation of subsonic longitudinal and lateral aerodynamic characteristics of slender sharp edge 74 deg swept wings -
NASA-TN-D-6391
Wind-tunnel investigation of an external-flow jet-flap transport configuration having full-span triple-slotted flaps -
NASA-TN-D-6440
Dynamic stability derivatives of a jet transport configuration with high thrust-weight ratio and an externally blown jet flap -
NASA-TN-D-6531
Comparison of several methods for estimating low speed stability derivatives -
NASA-TN-D-6573
Full-scale wind-tunnel tests of a small unpowered jet aircraft with a T-tail -
NASA-TN-D-6575
Summary of spin technology as related to light general-aviation airplanes -
NASA-TN-D-6643
Aerodynamic parameters of the Navion airplane extracted from flight -
NASA-TN-D-6777
Flight-determined derivatives and dynamic characteristics of the CV-990 airplane -
NASA-TN D-6800
Longitudinal aerodynamic characteristics of light, twin-engine, propeller-driven airplanes -
NASA-TN-D-6826
Wind-tunnel investigation at low speeds of a model of the Kestrel (XV-6A) vectored-trust V/STOL airplane -
NASA-TN-D-6866
Summary of design considerations for airplane spin-recovery parachute systems -
NASA-TN-D-6896
The effects of configuration changes on the aerodynamic characteristics of a full-scale mockup of a light twin engine airplane -
NASA-TN-D-6905
Lateral stability and control derivatives of a jet fighter airplane extracted from flight test data by utilizing maximum likelihood estimation -
NASA-TN-D-6909
Dynamic stability derivatives at angles of attack from minus 5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails -
NASA-TN D-6946
Lateral-directional aerodynamic characteristics of light, twin-engine, propeller driven airplanes -
NASA-TN-D-7099
Effect of wing design on the longitudinal aerodynamic characteristics of a wing-body model at subsonic speeds -
NASA-TN-D-7149
Wind tunnel investigation of static longitudinal and lateral characteristics of a full scale mockup of a light single engine high wing airplane -
NASA-TN-D-7163
Effects of fineness and closure ratios on boattail drag of circular-arc-afterbody models with jet exhaust at Mach numbers up to 1.3 -
NASA-TN-D-7185
Theoretical and experimental internal flow characteristics of a 13.97-centimeter-diameter inlet at STOL takeoff and approach conditions -
NASA-TN-D-7192
Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30 -
NASA-TN-D-7205
Effect of wing aspect ratio and flap span on aerodynamic characteristics of an externally blown jet-flap STOL model -
NASA-TN-D-7411
Free-flight investigation of the stability and control characteristics of a STOL model with an externally blown jet flap -
NASA-TN-D-7428
Low speed aerodynamic characteristics of a 17 percent thick airfoil section designed for general aviation applications -
NASA-TN-D-7429
Measured pressure distributions of large-angle cones in hypersonic flows of tetrafluoromethane, air, and helium -
NASA-TN-D-7455
Lateral static and dynamic aerodynamic parameters of the Kestrel aircraft (XV-6A) extracted from flight data -
NASA-TN-D-7613
High-temperature mass spectrometry - Vaporization of group 4-B metal carbides -
NASA-TN-D-7670
Longitudinal aerodynamic characteristics of an externally blown flap powered lift model with several propulsive system simulators -
NASA-TN-D-7716
Wind-tunnel free-flight investigation of a model of a spin-resistant fighter configuration -
NASA-TN-D-7721
Wind-tunnel investigation to determine the low speed yawing stability derivatives of a twin jet fighter model at high angles of attack -
NASA-TN-D-7739
Evaluation of importance of lateral acceleration derivatives in extraction of lateral-directional derivatives at high angles of attack -
NASA-TN-D-7921
Subsonic aerodynamic characteristics of interacting lifting surfaces with separated flow around sharp edges predicted by a vortex-lattice method -
NASA-TN-D-7972
Summary of information on low-speed lateral-directional derivatives due to rate of change of sideslip beta prime -
NASA-TN-D-8058
A review of the NASA V-G/VGH general aviation program -
NASA-TN-D-8090
A vortex-lattice method for the mean camber shapes of trimmed noncoplanar planforms with minimum vortex drag -
NASA-TN-D-8133
Low speed wind tunnel investigation of span load alteration, forward-located spoilers, and splines as trailing-vortex-hazard alleviation devices on a transport aircraft model -
NASA-TN-D-8136
Subsonic stability and control derivatives for an unpowered, remotely piloted 3/8-scale F-15 airplane model obtained from flight test -
NASA-TN-D-8206
Review of drag cleanup tests in Langley full-scale tunnel (from 1935 to 1945) applicable to current general aviation airplanes -
NASA-TN-D-8210
An experimental and analytical investigation of effect on isolated boattail drag of varying Reynolds numbers up to 130,000,000 -
NASA-TN-D-8236
Wind-tunnel investigation of a Fowler flap and spoiler for an advanced general aviation wing -
NASA-TN-D-8242
Aerodynamic characteristics of a vane flow angularity sensor system capable of measuring flight path accelerations for the Mach number range from 0.40 to 2.54 -
NASA-TN-D-8283
Landing practices of general aviation pilots in single-engine light airplanes -
NASA-TN-D-8351
Noise response of cavities of varying dimensions at subsonic speeds -
NASA-TN-D-8360
Low-speed wind-tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on a medium range wide-body tri-jet airplane model -
NASA-TN-D-8373
Low speed wind tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on an extended-range wide body tri-jet airplane model -
NASA-TN-D-8391
Calculations, and comparison with an ideal minimum, of trimmed drag for conventional and canard configurations having various levels of static stability -
NASA-TN-D-8524
Aerodynamic characteristics of wing-body configuration with two advanced general aviation airfoil sections and simple flap systems -
NASA-TP-1043
Effects of control inputs on the estimation of stability and control parameters of a light airplane -
NASA-TP-1306
Determination of stability and control parameters of a light airplane from flight data using two estimation methods -
NASA-TP-1350
Flight-determined stability and control derivatives for the F-111 Tact research aircraft -
NASA-TP-1419
Low-speed wind-tunnel parametric investigation of flight spoilers as trailing-vortex-alleviation devices on a transport aircraft model -
NASA-TP-1435
Similitude requirements and scaling relationships as applied to model testing -
NASA-TP-1498
Low-speed aerodynamic characteristics of a 13 percent thick medium speed airfoil designed for general aviation applications -
NASA-TP-1500
Estimation of attainable leading-edge thrust for wings at subsonic and supersonic speeds -
NASA-TP-1580
Low-speed aerodynamic performance of a high-aspect-ratio supercritical-wing transport model equipped with full-span slat and part-span double-slotted flaps -
NASA-TP-1592
Effects of fuselage forebody geometry on low-speed lateral-directional characteristics of twin-tail fighter model at high angles of attack -
NASA-TP-1619
Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies -
NASA-TP-1636
Measurement of the handling characteristics of two light airplanes -
NASA-TP-1652
Measured and predicted shock shapes and aerodynamic coefficients for blunted cones at incidence in air at Mach 5.9 -
NASA-TP-1786
Low-speed aerodynamic characteristics of a 17-percent-thick medium speed airfoil designed for general aviation applications -
NASA-TP-1865
Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications -
NASA-TP-1878
Experimental and theoretical supersonic lateral-directional stability characteristics of a simplified wing-body configuration with a series of vertical-tail arrangements -
NASA-TP-1889
Wing-alone aerodynamic characteristics for high angles of attack of supersonic speeds -
NASA-TP-1919
Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section -
NASA-TP-2005
Effects of axisymmetric and normal air jet plumes and solid plume on cylindrical afterbody pressure distributions at Mach numbers from 1.65 to 2.50 -
NASA-TP-2382
Wind-tunnel investigation of a full-scale canard-configured general aviation airplane -
NASA-TP-2478
Effect of aileron deflections on the aerodynamic characteristics of a semispan model of a subsonic energy-efficient transport -
NASA-TP-2683
Experimental cavity pressure distributions at supersonic speeds -
NASA-TP-2772
Wind-tunnel investigation of a full-scale general aviation airplane equipped with an advanced natural laminar flow wing -
NASA-TP-2990
Experimental and theoretical aerodynamic characteristics of a high-lift semispan wing model -
NASA-TP-3032
Experimental investigation of porous-floor effects on cavity flow fields at supersonic speeds -
NASA-TP-3099
Effects of yaw angle and Reynolds number on rectangular-box cavities at subsonic and transonic speeds -
NASA-TP-3110
Measurements of forces, moments, and pressures on a generic store separating from a box cavity at supersonic speeds -
NASA-TP-3133
Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoil -
NASA-TP-3358supp
Experimental cavity pressure measurements at subsonic and transonic speeds. Static-pressure results, supplement -
NASA-TP-3358
Experimental cavity pressure measurements at subsonic and transonic speeds. Static-pressure results -
NASA-TP-3557
Improved Method for Prediction of Attainable Wing Leading-Edge Thrust -
NASA-TP-3637
Guide to AERO2S and WINGDES Computer Codes for Prediction and Minimization of Drag Due to Lift -
NASA-TP-3669
Cavity Unsteady-Pressure Measurements at Subsonic and Transonic Speeds -
NASA-TR-R-50
Approximations for the Thermodynamic and Transport Properties of High-Temperature Air -
NASA-TR-R-57
Status of Spin Research for Recent Airplane Designs -
NASA-TR-R-171
The correlation of oblique shock parameters for ratios of specific heats from 5/3 with application to real gas flows -
NASA-TR-R-274
Experimentally determined local flow properties and drag coefficients for a family of blunt bodies at Mach numbers from 2.49 to 4.63 -
NASA-TR-R-300
Aerodynamic forces on a stationary and oscillating circular cylinder at high Reynolds numbers -
NASA-TR-R-374
Calculation of nonlinear conical flows by the method of lines -
NASA-TR-R-428
Extension of leading-edge-suction analogy to wings with separated flow around the side edges at subsonic speeds -
NASA-TR-R-433
Experimental determination of airplane mass and inertial characteristics -
NASA-TR-R-474
Prediction of static aerodynamic characteristics for slender bodies alone and with lifting surfaces to very high angles of attack -
NASA-TT-F-823
Theory of the lifting airscrew