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NACA 0012 Validation in SU2

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Old   July 27, 2016, 17:36
Default NACA 0012 Validation in SU2
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Dillon Thomison
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Howdy. I am a graduate student researching information fusion in multifidelity computer simulations. I'm using XFOIL and SU2 as low and high fidelity simulators, respectively. However, when validating the results for the NACA 0012 airfoil against the NASA data SU2 is not as accurate as XFOIL as shown in the attached plot of CL vs angle of attack.

How can I best modify the config file to produce a more accurate simulation? Should I be using a different mesh file other than the default one provided by SU2?

Any help would be greatly appreciated.
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Old   July 31, 2016, 16:03
Default NACA 0012 Validation in SU2
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Dillon Thomison
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Howdy. I was able to reproduce the NASA results and wanted to update this post in case anybody else needs to do the same. I used the RANS test case. The config file can be found in the SU2 directory, but the mesh file is in a separate TestCases directory.

Does anybody know where additional data can be found to validate at mach numbers higher than 0.15? I presume the SU2 team found some reliable data to validate SU2 against.

Thanks,
Dillon
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Old   August 2, 2016, 02:42
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Hi, I'm also using SU2 4.2.0 to validate the NACA0012 testcase, but my drag coefficient is higher than the NASA data, at(MA 0.15, RE 6e6, AOA 10degree), based on SA model the Cd is about 0.014585, what about your results?
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Old   August 6, 2016, 17:39
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Quote:
Originally Posted by rainbow0430 View Post
Hi, I'm also using SU2 4.2.0 to validate the NACA0012 testcase, but my drag coefficient is higher than the NASA data, at(MA 0.15, RE 6e6, AOA 10degree), based on SA model the Cd is about 0.014585, what about your results?
Howdy. My Cd results are not as good as I would hope either. I have attached a graph. I'm not sure how to make this more accurate.
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Old   August 25, 2016, 17:49
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Zach Davis
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You haven't completed a mesh convergence study. You don't know whether you're getting mesh independent results. See whether a finer grid provides a better answer...
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Old   December 20, 2016, 21:54
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Quote:
Originally Posted by rainbow0430 View Post
Hi, I'm also using SU2 4.2.0 to validate the NACA0012 testcase, but my drag coefficient is higher than the NASA data, at(MA 0.15, RE 6e6, AOA 10degree), based on SA model the Cd is about 0.014585, what about your results?
Hello Rainbow,
I was testing the same case as well, and I have been troubleshooting it for a while. Haven't solved the issue completely. Any progress have you made?

Thanks,
Paul
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Old   December 21, 2016, 22:29
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JAMES
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yes, i also find this problem. I compared the test case's rans RAE2822 examples results and it also can't fit the experiment results very well.
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Old   December 22, 2016, 02:37
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Originally Posted by yugang881 View Post
yes, i also find this problem. I compared the test case's rans RAE2822 examples results and it also can't fit the experiment results very well.
From my solution, it appears that the error comes from the trailing edge. Not quite sure it is the mesh part or something else.
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