hypersonic blunt cone boundary layer 高超声速钝锥边界层
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。
The nature of an open separation has been analysed qualitatively and the numerical simulation has been made for the hypersonic flow with an open separation over the blunt cone at Angle of attack.
本文定性分析了开式分离的性状，并对钝锥有攻角超声速绕流的开式分离作了数值模拟。
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