本文论述了入射激波与飞行器头部激波相交后的二维或轴对称干扰流场的计算方法。

This paper describes the numerical method determining two-dimensional and axisymmetric flow for head-on vehicle shock-planar incident shock interaction.

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本文从化学非平衡粘性激波层控制方程出发，用数值法计算了高超音速钝体绕流头部区流场(包括驻点线和音速线)。

In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region (including stagnation line and sonic line).

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