【摘要】 应用片条理论，将文献[1]的尖前缘任意翼型的俯仰稳定性导数的计算方法作了推广，用于计算任意平面形状的三维机翼。在各种特殊的情况下，其计算结果与现有的理论都符合得很好。在激波附体的条件下，本文的计算方法可用于计算任意边角、任意平面形状机翼的超、高超声速俯仰稳定性导数。更多还原

【Abstract】 Using strip theory, an approximate method is developed for predicting the aerodynamic stability of oscillating supersonic/hypersonic wings of arbitrary planform, which uses the unsteady flow solutions of Ref. [1] over an oscillating airfoil with pointed leading edge plus strip theory approximation to obtain the formulas for the stability derivatives.Good agreement is obtained with existing thoeries in various special cases. They are applicable for wings of arbitrary planform shape with pointed leading edge wing section at arbitrary angle of attack provided the shock wave is attached to the leading edge of the wing.更多还原