FLUENT TRANSITION WRONG?
I cannot seem to get the coefficient of drag for the NACA 0012 airfoil in my FLUENT 6.2 simulations. The drag coefficient differ alot from experimental data. My Y plus region was set to 1 . even then the drag is still high. Any help? I'm using a C grid mesh.
|
All times are GMT -4. The time now is 14:06. |