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)。
A simplified flow field model and simple air chemical model for the chemical nonequilibrium wakes of hypersonic non-ablating blunt-body are presented.
本文提出了一个高超声速非烧蚀钝体尾流全流场的简化模型和简化的空气化学模型。
According to the boundary layer character in reentry wake of hypersonic blunt cone body, this paper presents a local similar solution for hypersonic wake.
依据钝锥体再入远尾迹流动的边界层特征，从边界层方程出发得到了高超声速远尾迹流动的拟相似性解。
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