hello,

i've a fractional step FVM structured 2D NS solver. I'm now trying to solve the flow past a NACA0012 airfoil. I initially just calculate the top half since it's symmetrical. The flow field seems ok.

however now, I tried to simulate the full airfoil and large v velocities appear around the trailing edge region, especially the cells near the center line and just right of the trailing edge.

I've tried to scan for programming errors but I've yet to find any. I've also compared the sym and full answers but I can't find the error. Has anyone encounter similar problems before?

thanks

Sounds familiar....

Are you working on Dr. Lohner's project for the CFD class?

I assume you use C-type grid and special boundary treatment on the cuting edge sttarted from TE. Be sure if the BC is correctly implemented.

tiger: no

versi: I've used special BC for the cutting edge. I've got a symmetrical ans, everything seems "ok" except for large velocites at cells near trailing edge....