Abstract: 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.

Key words: Navier-Stokes equation, turbulent models, alternating direction implicitmethod 　computational grids