[liujmljm]

Dear, I try to simulate NACA0012 airfoil at AoA =10, Mach=0.15, Re=6e6. Based the grid provided at the folder of Testcase/rans/naca0012. The CL calculated by SU2 is about 0.4. But the right result should be about 1. Does anyone test the case? Thank you very much.
The configure file is attached.

[liujmljm]

The solver can not converge. Do we need use lower mach preconditioning.
Thank you

Originally Posted by liujmljm

Dear, I try to simulate NACA0012 airfoil at AoA =10, Mach=0.15, Re=6e6. Based the grid provided at the folder of Testcase/rans/naca0012. The CL calculated by SU2 is about 0.4. But the right result should be about 1. Does anyone test the case? Thank you very much.
The configure file is attached.

[fpalacios]

Hi,

I think there must be something wrong in the config file that you are using. Could you please try with the attached config file, the current developer's version of SU2 (you can fork the repository in https://github.com/su2code/SU2), and the grid TestCases/rans/naca0012/mesh_NACA0012_turb_897x257.su2.

The results (AoA =10, Mach=0.15, Re=6e6) are in a very good agreement with the experimental data (CL = 1.0989, CD = 0.0128). Note that the config file only works with the latest version of SU2.

Best,
Francisco

Originally Posted by liujmljm

Dear, I try to simulate NACA0012 airfoil at AoA =10, Mach=0.15, Re=6e6. Based the grid provided at the folder of Testcase/rans/naca0012. The CL calculated by SU2 is about 0.4. But the right result should be about 1. Does anyone test the case? Thank you very much.
The configure file is attached.