计算谐振机翼气动力的激波膨胀波级数展开法

本文根据激波-膨胀波理论,忽略了反射波对翼面压强分布的影响,把斜激波之后和通过一族主特征线的压强展成级数,给出了沉浮和俯仰谐振翼型表面压强分布的近似解析解。然后应用片条理论导得三维机翼振动导数的闭式解。文中给出三角形机翼俯仰导数的几个实例,数值结果与现有其它方法的结果有很好的一致性。

Series Expansion Method for Shock-Expansion Waves of Calculating Harmonical Oscillating Wing Aerodynamic Forces

On the basis of shock-expansion waves theory, neglecting reflective wave influence on pressure distribution over airfoil surface, and expanding pressure behind an oblique shock and through a single family of principle characteristics into a power series, an approximate analytical solution is given for airfoil surface pressure distribution in harmonically plunging and pitching oscillating.Then using strip theory, three-dimensional wing oscillating derivative closed solutions are developed. Several examples of pitching derivatives for delta wings are given, numerical results of this method are in agreement with the results of other methods.