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Can not get the right result at AoA=10 for RANS simulation of the NACA0012

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Old   August 18, 2013, 05:39
Default Can not get the right result at AoA=10 for RANS simulation of the NACA0012
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Jianming Liu
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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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File Type: txt naca0012.txt (10.0 KB, 5 views)
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Old   August 18, 2013, 08:51
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Jianming Liu
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The solver can not converge. Do we need use lower mach preconditioning.
Thank you
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Originally Posted by liujmljm View Post
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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Old   August 19, 2013, 01:25
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Francisco Palacios
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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 View Post
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.
Attached Files
File Type: txt default.txt (8.5 KB, 15 views)
fpalacios is offline   Reply With Quote

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