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Currently there is a renewed interest in the
aerothermodynamics of external flows about vehicles at very
high altitudes. The main factors are the development of
the space transportation system and the orbital transfer
vehicles. It is the purpose of this paper to conduct
numerical experiments for the hypersonic flow around two
diifferent shaped blunt bodies, rectangular shaped and
rounded shaped blunt bodies. The general flowfield information,
Mach number, pressure, density and tempature distributions
were calculated by using the continuum flow approach and the
molecular gas dynamics approach respectively. The MacCormack
implicit method and DSMC method are used. The change of
flow properties through shock and the effects of rare faction
under different Knudsen number will also be investigated in the
proposal.
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