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.

在不角变化的条件下，进气道不起动边界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.

在弹丸前体外形和外界大气密度不变的条件下，提出了利用弹丸炮口马赫数和顶点马赫数确定旋转弹丸最佳尾锥角的方法。

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件，进气道不起动边界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.

在弹丸前体外形和外界大气密度不变的件，提出了利用弹丸炮口马赫数和顶点马赫数确定旋转弹丸最佳尾锥角的方法。

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.

在弹丸前体形大气密度不变的条件下，提出了利用弹丸赫数顶点赫数确定旋转弹丸最佳尾锥角的方法。

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，进气道不起动边界主要与来流马有关。

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.

在弹丸前界大气密度不变的条件下，提出了利用弹丸炮口马顶点马确定旋转弹丸最佳尾锥角的方法。

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，进气道不起动边界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.

在弹外形外界大气密度不变的条件下，提出了利用弹炮口马赫数马赫数确定旋转弹最佳尾锥角的方法。

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.

在前体外形和外密度不变的条件下，提出了利用口马赫数和顶点马赫数确定旋转最佳尾锥角的方法。

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，进气道不起动边界主要与来流有关。

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.

在弹丸前体外形和外界大气密度不变的条件下，提出了利用弹丸炮口和顶点确弹丸最佳尾锥角的方法。

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.

在不考虑化的条件下，进气道不起动边界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.

在弹丸前体外形和外界大气密度不的条件下，提出了利用弹丸炮口马赫数和顶点马赫数确定旋转弹丸最佳尾锥的方法。

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，不起动边界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.

在弹丸前体外形和外界大密度不变的条件下，提出了利用弹丸炮口马赫数和顶点马赫数确定旋转弹丸最佳尾锥角的方法。