Numerical simulation of re-entry flow around the Space Shuttle with finite-rate chemistry

Abstract

Hypersonic flow around the Space Shuttle is computed for a series of re-entry flight conditions by incorporating a one-temperature model that takes into account 7-species finite-rate chemistry. An implicit higher-order upwind scheme based on a generalized Roe's approximate Riemann is used. The aerodynamic characteristics and heating rates are compared with the STS-2 flight data, and good agreement is obtained. These results quantitatively confirm the measured forward shift of the center of pressure and reduction of heating rates caused by real gas effects.