振动翼型跨音速非定常Euler方程数值解方法

NUMERICAL METHOD FOR SOLVING THE EULER EQUATION FOR UNSTEADY TRANSONIC FLOWS OVER OSCILLATING AIRFOILSS North-western Polytechnical University

通过坐标变换使变化的物面边界条件及无穷远边界条件变为固定的有限范围内的边界条件。因此可在不增加计算机时的情况下,边界条件可以精确地满足。由于主控方程是Euler方程,因此,凡适合于Euler方程解的问题(跨音速、大扰动、非定常、高简化频率)均可应用此法。同时,在计算过程中采用贴体、正交网格与可控网格技术获得最佳网格分布。算例计算结果是令人满意的。

Through transformations, the time-dependent boundary conditions on the airfoil contour and the boundary conditions at infinity are brought fixed to the boundaries of a finite domain. The boundary conditions can thus be satisfied exactly without increasing the computational time. The novel scheme is useful for computing transonic, strong disturbance, unsteady folws with high reduced frequencies. The scheme makes use of curvefitted orthogonal meshes and the lettice-control technique to obtain the optimal grid distribution. The numerical results are satisfactory.