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NACA Research Memorandums
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Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method
Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel
Altitude Cooling Investigation of the R-2800-21 Engine in the P-47G Airplane 4 - Engine Cooling-Air Pressure Distribution
Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine
Altitude-wind-tunnel investigation of various can-type burners in Bumblebee 18-inch ram jet
Amplitude of Supersonic Diffuser Flow Pulsations
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
Analytical investigation of effect of water-cooled turbine blades on performance of turbine-propeller power plants
Burning rates of single fuel drops and their application to turbojet combustion process
Calibration of Air-Flow Meters for J33 Compressor Investigation
Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude
Combined Compressor Coolant Injection and Afterburning for Turbojet Thrust Augmentation
Combined compressor coolant injection and afterburning for turbojet thrust augmentation
Combustion-Chamber Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel
Comparative Tensile Strengths at 1200 Degrees F of Various Root Designs for Cermet Turbine Blades
Comparison of ignition delays of several propellant combinations obtained with modified open-cup and small-scale rocket engine apparatus
Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound
Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6
Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6
Component performance investigation of L71 experimental turbine 10: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 132-percent-design stator area
Criterions for prediction and control of ram-jet flow pulsations
Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section
The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections
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