maximus

July 16, 2005 03:37 
About the invisd flow around an airfoil
Hi,I cam writing a code for compressible flow. In my code,I use the pressurebased method such as SIMPLE which has been extended to the compressible flow by including the density corrections. The code is orginally written for viscous flow by solving the NS equations, while I can get the invisid results by setting the viscosity equal zero. Untill now I have finished the validation computations such as the flow in a nozzle and flow in a tunnel with an arc bump, and the results are in good agreement with the results of other authors. But when I turn to the flow around an airfoil, I find that it doesn't work.In the computation, I use the firstorder upwind algorithm for the convetion terms. After carefully debuging, I find that the coefficients of the discretized momentum equations are zero in some nodes near the wall in the staganation region which terminated the computation. I try to solve this problem by set the coefficient to be 1e30 when it is zero, but it doesn't work. Because there is no diffusion term in the invisd solution,so in the stagnation region there is the possiblity for the coeefficents to be zero when the flow is reverse to the wall at the begining of the computation. I don't know how to deal with this problem, so I wonder if anybody can give me some suggestions. I will be very grateful for any suggestions. Thanks!!
