用当地流活塞理论计算大攻角翼面超音速颤振

SUPERSONIC FLUTTER CALCULATION OF A WING WITH ATTACK ANGLE BY LOCAL FLOW PISTON THEORY

本文应用当地流活塞理论，推导了弹性振动翼面的非定常压力分布以及用模态坐标表示的广义气动力系数矩阵，相应的颤振运动方程和特征方程，提出了可用于大攻角、有限厚度翼面超音速颤振计算的一种新的工程计算方法。算例表明方法的可行性和工程实用价值。

In this paper a new engineering approach is presented of flutter analysis by the local flow piston theory. Corresponding pressure distribution of unsteady flow for wing with elastic vibration, general aerodynamical coefficient matrix using modal coodinate, motion equation of flutter and flutter eigenequation are deduced. This method is available for supersonic flutter calculation of wing with attack angle and finite thickness. The results from numerical example show that this method is effective and practical value for engineering aplication.