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The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight

Author: Richard Scherrer

Publisher:

Published: 1947

Total Pages: 542

ISBN-13:

An approximate method for determining the convective cooling requirement in the laminar-boundary-layer region of a body of revolution in high-speed flight was developed and applied to an example body. The cooling requirement for the example body was determined as a function of Mach number, altitude, size, and a surface-temperature parameter. The maximum value of Mach number considered was 3.0 and the altitudes considered were those within the lower constant-temperature region of the atmosphere (40,000 to 120,000 ft). The extent of the laminar boundary layer was determined approximately at each condition as a function of the variables considered.

Calculation of Surface Temperatures in Steady Supersonic Flight

Author: George P. Wood

Publisher:

Published: 1946

Total Pages: 34

ISBN-13:

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Surface temperatures were calculated for bodies in steady supersonic flight at Mach numbers from 2 to 10 and for altitudes from 50,000 and 200,000 feet and emissivities from 0 to 1. The importance of the effects of radiation and convection was determined. It was found, under the assumption of an isothermal atmosphere, that the gain of heat from the air by convection decreases at constant Mach number as the altitude is increased. Equilibrium between convection and radiation is established at temperatures that that consequently decrease as altitude is increased. In general, therefore, at sufficiently high altitudes the surface temperature is considerably less than the stagnation temperature. At a Mach number of 8, for example, the stagnation temperature is 4800 degrees F absolute and the equilibrium surface temperature for an emissivity of 0.5 is 3800 degress F absolute at 50,000 feet and decreases to 1350 degrees F at 200,000 feet.