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).
在热化学非平衡流情况下，经典的粘性相互作用参数和经验公式具有局限性。
The classical viscous interaction parameter and experiential formulae are limitative in thermochemical nonequilibrium flow.
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