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NACA Research Memorandums
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Effect of Distributed Granular-Type Roughness on Boundary-Layer Transition at Supersonic Speeds With and Without Surface Cooling
Experimental Lift-Drag Ratios for Two Families of Wing-Body Combinations at Supersonic Speeds
Longitudinal and Lateral Stability and Control Characteristics at Mach Number 2.01 of a 60 Degree Delta-Wing Airplane Configuration Equipped With a Canard Control and With Wing Trailing-Edge Flap Controls
Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30-Degree Blunted Nose Cone
Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls
Additional Fatigue Tests on Effects of Design Details in 355-T6 Sand-Cast Aluminum Alloy
Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61
An air-flow-direction pickup suitable for telemetering use on pilotless aircraft
Evaluation of Altitude-Ignition Characteristics of Three Fuels of Different Volatility in a Turbojet Engine
Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer
Investigation of Three Low-Temperature-Ratio Combustor Configurations in a 48-Inch-Diameter Ram-Jet Engine
Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine
Kinetic study of mass transfer by sodium hydroxide in nickel under free-convection conditions
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet
Design and Test of Mixed-Flow Impellers 3: Design and Experimental Results for Impeller Model MFI-2A and Comparison With Impeller Model MFI-1A
Investigation of Turbines for Driving Supersonic Compressors 3: First Configuration With Four Nozzle Settings and One Nozzle Modification
Investigation of water-spray cooling of turbine blades in a turbojet engine
Some Measurements of Flying Qualities of a Douglas D-558-II Research Airplane During Flights to Supersonic Speeds
A Transonic Wind-Tunnel Investigation of the Effects of Longitudinal Wing Location and Varying Body Size on the Interference Characteristics of a 45 Degrees Sweptback Wing
Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers 1: over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1
Facilities and methods used in full-scale airplane crash-fire investigation
Investigation in the Ames Supersonic Free-Flight Wind Tunnel of the Static Longitudinal Stability of the Hermes A-3B Missile at a Mach Number of 5.0
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback: Estimated Downwash Angles Derived From Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59
Studies of the flow field behind a large scale 47.5 degree sweptback wing having circular-arc airfoil sections and equipped with drooped-nose and plain flaps
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