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Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)

Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04

Exploratory Investigation of Transpiration Cooling to Alleviate Aerodynamic Heating on an 8 Degree Cone in a Free Jet at a Mach Number of 2.05

Exploratory Tests of Transpiration Cooling on a Porous 8 Degree Cone at M = 2.05 Using Nitrogen Gas, Helium Gas, and Water as the Coolants

Turbulent Convective Heat-Transfer Coefficients Measured From Flight Tests of Four Research Models (NACA RM-10) at Mach Numbers From 1.0 to 3.6

Aerodynamic heating of aircraft components

Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)

Temperature measurements from a flight test of two wing-body combinations at 7 degree angle of attack for Mach numbers to 4.86 and Reynolds numbers to 19.2 X 10(exp 6)

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 Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Measurement of Aerodynamic Heat Transfer to a Deflected Trailing-Edge Flap on a Delta Fin in Free Flight at Mach Numbers From 1.5 to 2.6

Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70

Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone


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