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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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NACA Research Memorandums
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National Advisory Committee for Aeronautics Collection
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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) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies
An experimental cascade study of the effects of a solidity reduction on the two-dimensional aerodynamic characteristics of a turbine-rotor blade suitable for air cooling
A Comparison of Flight-Measured Carrier-Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components
Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs
Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter
Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone
Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers
An empirically derived basis for calculating the area, rate, and distribution of water-drop impingement on airfoils
Tests of Air Valves for Intermittent-Jet Engines at Speeds of 20 and 25 Cycles Per Second
Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds
Characteristics of perforated diffusers at free-stream Mach number 1.90
Sound from a two-blade propeller at supersonic tip speeds
Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter
A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
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