24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-3.7.4 (St.)

COMPUTATIONAL STUDY OF CHEMICALLY REACTING HYPERSONIC FLOW

Y. Funahashi
Department of Aeronautics and Astronautics, Graduate School of Engineering, The University of Tokyo, Tokyo, Japan

Keywords: hypersonic flow, chemical equilibrium, thermal protection

Because space vehicles reentering the Earth’s atmosphere are exposed to immense aerodynamic heating, so some kinds of thermal protection systems are indispensable. Computational analysis of two kinds of thermal protection systems, that is, the film cooling and the transpiration cooling, was conducted, taking real gas effects into account.

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