NACA 0012 Validation in SU2

wdillon44 · July 27, 2016, 18:36

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.

wdillon44 · July 31, 2016, 17:03

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

rainbow0430 · August 2, 2016, 03:42

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?

wdillon44 · August 6, 2016, 18:39

Quote:

Originally Posted by rainbow0430

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.

RcktMan77 · August 25, 2016, 18:49

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...

paulzhang · December 20, 2016, 21:54

Quote:

Originally Posted by rainbow0430

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

yugang881 · December 21, 2016, 22:29

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.

paulzhang · December 22, 2016, 02:37

Quote:

Originally Posted by yugang881

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.

July 31, 2016, 17:03	NACA 0012 Validation in SU2	#2
wdillon44 New Member Dillon Thomison Join Date: Jul 2016 Posts: 3 Rep Power: 10	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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August 2, 2016, 03:42		#3
rainbow0430 New Member Join Date: Apr 2016 Posts: 1 Rep Power: 0	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?

August 25, 2016, 18:49		#5
RcktMan77 Senior Member Zach Davis Join Date: Jan 2010 Location: Los Angeles, CA Posts: 101 Rep Power: 16	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...

December 21, 2016, 22:29		#7
yugang881 New Member JAMES Join Date: Dec 2016 Posts: 21 Rep Power: 9	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.