The interaction between an oblique blast wave and supersonic blunt cone was discussed.
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。
This paper presents experimental results of flap heat transfer and pressure characteristics on a blunt cone in shock tunnel.
本文介绍了一种在激波风洞中取得的，装在钝锥模型上的控制翼热流及压力特性实验结果。
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。
The Rayleigh inverse-iteration method and boundary layer asymptotic expansion method are used to solve the blunt cone boundary layer stability equation to get reliable boundary layer transition data.
然后应用反迭代法与边界层渐近匹配的方法求解了钝锥边界层的稳定性方程，得到了钝锥边界层转捩数据。
Roll torque is produced due to the effects of circumferential lag of ablation for a spinning blunt-nosed cone at angles of attack.
有迎角的旋转钝锥由于周向烧蚀滞后将产生滚转力矩。
The chosen vehicles are a blunt bi cone with cruciform flaps and a variable bent axis vehicle.
所研究的气动外形为带控制舵飞行器和可变弯体飞行器。
The chosen vehicles are a blunt bi cone with cruciform flaps and a variable bent axis vehicle.
所研究的气动外形为带控制舵飞行器和可变弯体飞行器。
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