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NACA Research Memorandums
28
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NACA Research Memorandums
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1953
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1953
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NACA Research Memorandums
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Evaporation and Spreading of Isooctane Sprays in High Velocity Air Streams
Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application
Jet effects on flow over afterbodies in supersonic stream
Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18
Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound
Free-Jet Investigation of a 20-Inch Ram-Jet Combustor Utilizing High-Heat-Release Pilot Burner
Flight Investigation of Nine Reduced-Scale (1:3.75) Hermes A-2S Rocket-Motor Test Vehicles
Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination
Notes on the prediction of shock-induced boundary-layer separation
Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine
Burning rates of single fuel drops and their application to turbojet combustion process
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 13: Endurance Evaluation of Several Protective Coatings Applied to Turbine Blades of Nonstrategic Steels
Preliminary Transient Performance Data on the J73 Turbojet Engine 2 - Altitude, 35,000 Feet
Preliminary Transient Performance Data on the J73 Turbojet Engine, 3: Altitude, 45,000 Feet
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
The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34
The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10-Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34 : TED No. NACA DE 31
Investigation of the Attenuation of Plane Shock Waves Moving Over Very Rough Surfaces
Preliminary Results From a Limited Investigation of the Use of Controls During Service Operational Training With Fighter Airplanes
Rocket-Model Investigation of the Longitudinal Stability, Drag, and Duct Performance Characteristics of the North American MX-770 (X-10) Missile at Mach Numbers from 0.80 to 1.70
Investigation of distribution of losses in a conservatively designed turbine
Thermal-Shock Resistance of a Ceramic Comprising 60 Percent Boron Carbide and 40 Percent Titanium Diboride
Experimental Investigation of the Aerodynamic Characteristics of an Air-to-Air Missile Employing Cruciform Wings and Tail of Rectangular Plan Form at Mach Numbers of 1.4 and 1.9
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