The fore-body with sharp section angle can produce direction stability at middle-higher angle of attack in the case of side-slip.
有侧滑时，尖侧缘的非圆截面机身头部在中等和大迎角下，可具有方向稳定性。
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)。
It is demonstrated that there exists a part of high pressure on the body surface of the rocket near the fore-located nozzles, thus forming a overturning moment.
指出，当超音速飞行时，在前喷管附近的弹体表面上产生一个局部高压区，由此形成一个翻转力矩。
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