[shsreekanth]

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
Cd= 0.019274
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.

[fpalacios]

Hi,

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,
Best,
Francisco

Originally Posted by shsreekanth

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
Cd= 0.019274
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.