Aerodynamic sensitivity for subsonic lifting-surface with arbitrary curved leading edge is evaluated by kernal function method.
具有任意曲线前缘的亚音速升力面的气动敏感性导数由核函数法给出。
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。
In this paper, separation control on Joukowsky airfoil having leading edge rotational cylinder is investigated by numerical simulation method.
本文使用数值模拟方法研究了活动翼面对翼型背风面分离的控制作用。
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