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NACA Research Memorandums
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A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
Local Isotropy in Turbulent Shear Flow
A Preliminary Investigation of High-Speed Impact the Penetration of Small Spheres Into Thick Copper Targets
Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes
Induction system characteristics and engine surge occurrence for two fighter-type airplanes
Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 employing high-velocity blowing over the leading- and trailing-edge flaps
Some Effects of Roughness on Stagnation-Point Heat Transfer at a Mach Number of 2, a Stagnation Temperature of 3,530 F, and a Reynolds Number of 2.5 X 10(Exp 6) Per Foot
Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
Theoretical analysis of the interference effects of several supersonic-tunnel walls capable of absorbing the shock caused by the nose of a model
Wind-Tunnel Investigation at a Mach Number of 2.01 of Forebody Strakes for Improving Directional Stability of Supersonic Aircraft
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 4: rotor loss patterns as determined by hot-wire anemometers with rotor operating in a circumferentially uniform inlet flow field
Investigation of two-stage counterrotating compressor 4: over-all performance of compressor with modified second-stage rotor
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Relation between flow range and other compressor-stage characteristics
Theoretical Rocket Performance of Liquid Methane with Several Fluorine-Oxygen Mixtures Assuming Frozen Composition
Performance of a 28-inch ramjet utilizing gaseous hydrogen at a Mach number of 3.6, angles of attack up to 12 degree, and pressure altitudes up to 110,000 feet
Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet
Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01
Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 degree delta wing at Mach numbers of 1.61 and 2.01
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