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。
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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).
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.