In this paper, the special evolution of disturbances in hypersonic blunt cone boundary layer with the oncoming flow of Mach 6 and semi-angle of 5 degree was investigated by direct numerical simulation (DNS).
本文对来流马赫数为6,半锥角为5度的钝锥边界层中扰动的空间演化进行了直接数值模拟。
参考来源 - 高超音速钝锥边界层中扰动演化的数值研究·2,447,543篇论文数据，部分数据来源于NoteExpress
有迎角的旋转钝锥由于周向烧蚀滞后将产生滚转力矩。
Roll torque is produced due to the effects of circumferential lag of ablation for a spinning blunt-nosed cone at angles of attack.
本文讨论了斜爆炸波与超音速钝锥激波层的相互作用问题。
The interaction between an oblique blast wave and supersonic blunt cone was discussed.
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。
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.
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