Viscous flow over naca0012 airfoil
I am new to CFD and SU2. I had gone through the tutorials in the SU2 website.
I am trying to find the Cl and Cd for flow over NACA0012 airfoil (using the same mesh given in test cases for inv_naca0012) .
For angle of attack = 0 deg, i get
Cl= - 0.001625
The Cd value is significantly high compared to NACA report which is around Cd=0.006.
The configuration file is attached ( in txt format). Kindly tell me what are the mistakes I have done.
To run a RANS problem you need an a-priori adapted grid in the boundary layer. You will find those grids in the TestCases/rans folder
Thanks for using SU2,
|All times are GMT -4. The time now is 20:56.|