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NACA Research Memorandums
35
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NACA Research Memorandums
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1951
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Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the D-558-I Research Airplane Through a Mach Number Range of 0.80 to 0.89 and Throughout the Normal-Force-Coefficient Range at Mach Numbers of 0.61, 0.70, 0.855, and 0.88
Some low-speed characteristics of an air-induction system having scoop-type inlets with provisions for boundary-layer control
Tank investigation of the Grumman JRF-5 airplane with a single hydro-ski and an extended afterbody
Stability and control characteristics at low speed of a 1/5-scale model of the Edo 142 hydro-ski research airplane
An Investigation of the Longitudinal Characteristics of the X-3 Configuration With Wing and Horizontal Tail Surfaces of Aspect Ratio 3.0 by Means of Rocket-Propelled Models: Results at High Lift Coefficients
Investigation of mechanisms of blade failure of forged Hastelloy B and cast Stellite 21 turbine blades in turbojet engine
Investigation of Minimum Drag and Maximum Lift-Drag Ratios of Several Wing-Body Combinations Including a Cambered Triangular Wing at Low Reynolds Numbers and at Supersonic Speeds
Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick rounded nose section
Buffeting-Load Measurements on a Jet-Powered Bomber Airplane With Reflexed Flaps
Correlation of Analog Solutions With Experimental Sea-Level Transient Data for Controlled Turbine-Propeller Engine, Including Analog Results at Altitudes
An investigation of single-degree-of-freedom snaking oscillations on a model of a high-speed research airplane by the NACA wing-flow method
Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method
Preliminary Investigation of the Supersonic Flow Field Downstream of Wire-Mesh Nozzles in a Constant-Area Duct
Investigation of a triangular wing in conjunction with a fuselage and horizontal tail to determine downwash and longitudinal-stability characteristics: transonic bump method
Two-dimensional cascade investigation of the maximum exit tangential velocity component and other flow conditions at the exit of several turbine blade designs at supercritical pressure ratios
Low-Speed Characteristics of a 45 Degree Swept Wing with Leading-Edge Inlets
Data presentation of force characteristics of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0
Calculated Aerodynamic Loadings of M, W, and Delta Wings in Incompressible Flow
Preliminary Experimental Investigation of Flutter Characteristics of M and W Wings
Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method
Preliminary evaluation of the air and fuel specific-impulse characteristics of several potential ram-jet fuels 4: hydrogen, a-methylnaphthalene, and carbon
Free-Spinning-Tunnel Investigation to Determine the Effect of Two Nose Designs on Spin and Recovery Characteristics of a 1/20-Scale Model of the McDonnel XF3H-1 Airplane: TED No. NACA DE 343
Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting free-floating fuel tanks attached to the wing tips
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