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Research Papers

Analysis of the Aerodynamic Heating for a Re-Entrant Space Vehicle

[+] Author and Article Information
M. J. Brunner

Advanced Studies, Thermodynamic Engineering, General Electric Company, Missiles and Space Vehicle Department, Philadelphia, Pa.

J. Heat Transfer 81(3), 223-229 (Aug 01, 1959) (7 pages) doi:10.1115/1.4008191 History: Received December 02, 1958; Published August 01, 1959; Online February 19, 2019

Abstract

An analysis of the aerodynamic heating is presented through the trajectory and over the surface of a re-entrant hypersonic space vehicle. Bodies exhibiting zero and high lift over drag ratios are considered. The turbulent and laminar convective heat inputs are specified as functions of the trajectory and space vehicle parameters. The maximum heating rates and time integrated heat fluxes are given as functions of the local pressure distribution, body geometry, and wall temperature. Examples are presented to illustrate the application of this analysis.

Copyright © 1959 by ASME
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