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NACA Research Memorandums
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Full-Scale Wind-Tunnel Tests of a 35 Degree Swept-Wing Fighter Airplane With a Spoiler-Slot-Deflector Lateral Control System
Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution
An Investigation of Ejection Releases of Submerged and Semisubmerged Dynamically Scaled Stores From a Simulated Bomb Bay of a Fighter-Bomber Airplane at Supersonic Speeds
Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes
Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.89
Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage
Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01
Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds
Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag
Preliminary Tank Tests of NACA Hydro-Skis for High-Speed Airplanes
Numerical solution of equations for one-dimensional gas flow in rotating coolant passages
Supplementary analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass and aerodynamic parameters
The effects of compressibility on the pressures on a body of revolution and on the aerodynamic characteristics of a wing-nacelle combination consisting of the body of revolution mounted on a swept-back wing
Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models
Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Pitch of an NACA 64-Series 40 Degree Swept-Back Wing
Comparison between flight-measured and calculated span load distribution at high Mach numbers
Wind-Tunnel Investigation at Low Speeds of Various Plug-Aileron and Lift-Flap Configurations on a 42 Degree Sweptback Semispan Wing
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at a Mach number of 1.53 including effect of small variations of sweep
Inlet Icing and Effectiveness of Hot-Gas Bleedback for Ice Protection of Turbojet Engine
Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 2: nacelle with long straight air inlet
Effects of systematic changes of trailing-edge angle and leading-edge radius on the variation with Mach number of the aerodynamic characteristics of a 10-percent-chord-thick NACA airfoil section
Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 2: 18.41-Inch-Diameter Jet Nozzle
Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil
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