亜音速流中の2次元操舵面振動翼の高精度数値計算法

抄録

A numerical method is presented for the prediction of unsteady loadings on lifting airfoils that are due to oscillations of trailing edge control surfaces in subsonic compressible flow. An asymptotic pressure distribution is used to remove and separately evaluate the singularity in the kinematic downwash distribution. The method gives accurate result, quick convergence and excellent computational efficiency to other current methods.