马赫数

The results show that the unstart boundary of supersonic inlets is mainly concerned with Mach number of freestream without considering the variation of angle of attack.

在不考虑攻角变化的条件下，进气道不起动边主要与来流马赫数有关。

On condition that the front body shape of the projectile is unchangeable,a formula is obtained for determining the relation between the optimum boattail angle and the supersonic flight region.

在弹前体形和气密度不变的条件下，提出了利用弹马赫数和顶点马赫数确定旋转弹最佳尾锥角的方法。