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NACA Research Memorandums
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NACA Research Memorandums
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1954
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1954
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Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20
Investigation of a 10-stage subsonic axial-flow research compressor 4: performance evaluation and flow distributions in the first, fifth, and tenth stages
Performance of Isentropic Nose Inlets at Mach Number of 5.6
Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2
Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels
Preliminary investigation of performance and starting characteristics of liquid fluorine: Liquid oxygen mixtures with jet fuel
Review of High-Performance Axial-Flow-Compressor Blade-Element Theory
Performance of Isentropic Nose Inlets at Mach Number of 5.6
Effect of channel geometry on the quenching of laminar flames
Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 1: performance of rotor alone
Preliminary Wind Tunnel Investigation of Two Types of Jet-Exit Configurations for Control of Aircraft
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 5: aerodynamic load distributions for a series of four boattailed bodies
Tests in the Ames 40- by 80-Foot Wind Tunnel of the Aerodynamic Characteristics of Airplane Models With Plain Spoiler Ailerons
Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons
Longitudinal aerodynamic characteristics to large angles of attack of a cruciform missile configuration at a Mach number of 2
Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
Effects of leading-edge chord extensions and an all-movable horizontal tail on the aerodynamic characteristics of a wing-body combination employing a triangular wing of aspect ratio 3 mounted in a high position at subsonic and supersonic speeds
The Application of a Simplified Lifting-Surface Theory to the Prediction of the Rolling Effectiveness of Plain Spoiler Ailerons at Subsonic Speeds
Experimental investigation of effects of primary jet flow and secondary flow through a zero-length ejector on base and boattail pressures of a body of revolution at free-stream Mach numbers of 1.62, 1.93, and 2.41
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