在激波附体的条件下，本文的方法可用于计算大迎角尖前缘任意翼型的超音速和高超音速俯仰安定性导数。
This method may be used to calculate the arbitrary airfoils with sharp leading edge provided that the shock wave is attached.
在激波附体的条件下，本文的方法可用于计算大迎角尖前缘任意翼型的超音速和高超音速俯仰安定性导数。
This method may be used to calculate the arbitrary airfoils with sharp leading edge provided that the shock wave is attached.
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