Abstract
A computer program for accurately estimating the static aerodynamic characteristics of a slender, ablating re-entry vehicle is described. The approach includes a complete coupling between the flowfield analysis and the thermochemical analysis of the response of the heat shield material to the external environment. Moderate angles of attack and Mach numbers ranging from supersonic to hypersonic are considered. The transient thermochemical analysis provides values of wall temperature, mass ablation rate, and recession rate which are used to modify the vehicle shape and perform the flowfield calculations at the next trajectory point.
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