可压缩粘性流绕翼型的N─S方程自适应网格解

ADAPTIVE GRID SOLUTION OF N S EQUATION FOR COMPRESSIBLE VISCOUS FLOW AROUND AIRFOILS

从Ｎ－Ｓ方程出发，采用ＬＵ－ＡＤＩ隐式分解方法求解绕翼型的可压缩粘性流动。湍流模式采用Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模式和ｑ－ω二方程微分模式以研究湍流边界层的非平衡效应；为更好地捕捉激波，对网格进行了自适应调整。通过对ＮＡＣＡ００１２和ＲＡＥ２８２２两种翼型在亚音速和跨音速不同马赫数和雷诺数下进行大量计算，表明该方法对改进湍流计算。

Compressible viscous flow around airfoils, using LU ADI factorization difference method based on N S equations was computed. The two turbulent models (Baldwin Lomax algebraic model and q ω two equation model) were used to study the nonequilibrium effect of the turbulent boundary layer. In order to catch shock waves more efficiently, the technique of tension and torsion spring analogies was used to adjust the grids. Examples were included for both subsonic and transonic viscous flow around two airfoils NACA 0012 and RAE 2822 with different Mach numbers and Reynolds numbers. The computational results showed that the method in the paper could improve the turbulent computation and the ability of catching shock waves.