本文采用压强极小积分有限元法计算了NACA 0012翼型的跨音速流场。出发方程为全速位方程。
The transonic flow field around NACA 0012 airfoil is calculated by finite element method from pressure minimum integration, full potential equation being used.
求解全三维 N-S方程，通过高分辨率格式提高跨音速流场计算的准确性，利用 LU-SGS隐式解法加快计算收敛速度。
Three dimensional Navier-Stokes equations were solved. The accuracy was improved with a high-resolution scheme. And the convergence was speeded up by the use of LU-SGS implicit method.
分别对可压缩叶栅流场的亚音速和跨音速流动进行了数值模拟计算。
Some cases of compressible flow as well as incompressible flow are presented.
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