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NACA Research Memorandums
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NACA Research Memorandums
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1957
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1957
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NACA Research Memorandums
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1957
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Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8
Injection Principles for Liquid Oxygen and Heptane Using Nine-Element Injectors in an 1800-Pound-Thrust Rocket Engine
Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 2: design and experimental performance of turbine with low-velocity-turning stator and standard rotor
Reaction of Fluorine With Carbon as a Means of Fluorine Disposal
Reaction of Fluorine With Carbon as a Means of Fluorine Disposal
Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine
Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7
Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)
Heat-Transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2
Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88
Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310 and 3,500 Degrees R on a Magnesium Fin With Several Leading-Edge Modifications
Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0
Component performance investigation of J71 experimental turbine 8: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 70-percent-design stator area
Effect of burner design variables on performance of 16-inch diameter ram-jet combustor using gaseous-hydrogen fuel
Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed
Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06
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