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poor results of RAE2822
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I am running a case of RAE2822 airfoil with the grid file and cfg file in the TestCases folder, but it seems that I didn't get a good pressure distribution result compared to the experimental result in the same foler. I have uploaded a figure show the result. Besides, when I changed the mach number to 0.734 and AOA to 2.79 deg, none of SST and SA results converge!
I would appreciate any help, thanks. |
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