In this paper, the nonequilibrium viscous shocklayer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region (including stagnation line and sonic line).
One of the more severe fluctuating pressure environments encountered in supersonic or hypersonic flows is the shock wave oscillation driven by interaction of a shock wave with boundary layer.
在超声速或高超声速绕流中,一种很严重的脉动压力环境是由激波边界层相互作用引起的激波振荡。
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The problems of physical distortion due to the finite-difference scheme are studied in numerical solutions of the hypersonic viscous shock-layer equations.