The results show that the shock wave structure is unsteady in shock induced hypersonic turbulent separated flows, generating an intermittent region.

结果表明：在激波诱导的高超音速湍流分离流中，激波结构是不稳定的，产生一个间歇区域。

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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).

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)。

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