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
的条件下，进气道不
动边界主要与来流
有关。
（相当于声速的飞行速度）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.
在不考虑攻的条件下，进气道不动边界主要与来流有关。
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