Abstract

Recent studies have shown that for sufficiently high re-entry speeds, radiation energy transfer from high temperature air becomes an appreciable part of the total energy transfer to the nose of the re-entry body. This note is concerned with the effects of this fluid energy loss on the energy distribution in the shock layer and, therefore, on the convective and radiative fluxes at the wall. A nondimensional parameter is shown to govern the resulting coupling between radiative and convective fluxes. The first approximation which consists in assuming a constant stagnation temperature layer is shown to be acceptable for most ballistic and earth satellite re-entry problems. For larger velocities or dimensions (e.g., planetary probes and heavy meteors), radiation losses become important and it is necessary to include the radiation terms into the equations which determine the flow field.

*1 The work described in this note was conducted by the author for the Bendix Corporation and was supported by the United States Army Rocket and Guided Missile Agency, under contracts Nos. DA-11-022-ORD-2642 and DA-11-022-ORD-3130.

Consultant, Bendix Systems Division of Bendix Corporation.