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NACA Research Memorandums
269
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NACA Research Memorandums
269
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1949
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1949
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Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane
Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor
A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings
Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches
Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate
Preliminary Investigation of a Variable Mass-Flow Supersonic Nose Inlet
Comparative Tests of the Rolling Effectiveness of Constant-Chord, Full-Delta, and Half-Delta Ailerons on Delta Wings at Transonic and Supersonic Speeds
Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction
The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees
An empirical criterion for fin stabilizing jettisonable nose sections of airplanes
Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane
Full-Scale Hydrodynamic Evaluation of a Modified Navy J4F-2 Amphibian with a 0.425-Scale XP5M-1 Hull Bottom: TED No. NACA DE325
Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Effects at Subsonic Speeds of a Constant-Chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
Investigation of altitude performance of AN-F-58 fuels in annular combustor of J34-WE-22 engine
Survey of two-dimensional data on pitching-moment changes near maximum lift caused by deflection of high-lift devices
Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter
Spin-Tunnel Investigation of the Jettisoning of External Fuel Tanks in Spins
Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle
Altitude-wind-tunnel investigation of compressor performance on J47 turbojet engine
Low-speed pressure-distribution and flow investigation for a large pitch and yaw range of three low-aspect-ratio pointed wings having leading edge swept back 60 degrees and biconvex sections
Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. 4 - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second
Study of the canard configuration with particular reference to transonic flight characteristics and low-speed characteristics at high lift
Altitude-wind-tunnel investigation of J47 turbojet-engine performance
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