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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Technical Report Archive and Image Library
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Effect of three flame-holder configurations on subsonic flight performance of rectangular ram jet over range of altitudes
A Study of Several Parameters Controlling the Trajectories of a Supersonic Antiaircraft Missile Powered With Solid- or Liquid-Fuel Rockets
Lateral and directional stability and control characteristics of a C-54D airplane
Investigation of spark gaps subjected to altitude and air velocity conditions
Current Status of Longitudinal Stability
Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)
Visual Observations of the Shock Wave in Flight
Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats
Experimental pressure distribution on a asymmetrical nonconical body at Mach number 1.90
Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section: Transonic-Bump Method
Wind-tunnel investigation of a tailless triangular-wing fighter aircraft at Mach numbers from 0.5 to 1.5
Investigation of performance of Bumblebee 18-inch ram jet with a can-type flame holder
Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification
Effects of Chord Discontinuities and Chordwise Fences on Low-Speed Static Longitudinal Stability of an Airplane Model Having a 35 Degree Sweptback Wing
Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons
Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds
A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf
Determination and Use of the Local Recovery Factor for Calculating the Effectiveness Gas Temperature for Turbine Blades
Correlation of Analog Solutions With Experimental Sea-Level Transient Data for Controlled Turbine-Propeller Engine, Including Analog Results at Altitudes
Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls with Application to Turbine Blade Cooling
Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls
Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 4: effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed
Performance characteristics of canard-type missile with wing-mounted nacelle engines at Mach numbers 1.5 to 2.0
Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90
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