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-   -   Can not get the right result at AoA=10 for RANS simulation of the NACA0012 (http://www.cfd-online.com/Forums/su2/122363-can-not-get-right-result-aoa-10-rans-simulation-naca0012.html)

liujmljm August 18, 2013 05:39

Can not get the right result at AoA=10 for RANS simulation of the NACA0012
 
1 Attachment(s)
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 August 18, 2013 08:51

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

Originally Posted by liujmljm (Post 446393)
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 August 19, 2013 01:25

1 Attachment(s)
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



Quote:

Originally Posted by liujmljm (Post 446393)
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.



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