Issue with transition models
Im trying to simulate a 2D flow around the S809 airfoil (see attached picture). Flow reynolds number is 2 million (2D grid with unity depth). Im using the SST gama theta transition model for my simulation, currently I have been faced with an unknown problem. A grid consisting of 1 million elements was used. The simulation was run for 5000 iterations (convergence history is attached). The turbulence intensity of 0.03% was used. Unusually the wall shear stress distribution (see attached picture) suggests a cross flow between the two ends of the wing (symmetry conditions). Because of this two different distribution of shear stress is obtained at the suction(top) surface. I was wondering if anyone else faced the same issue with the gama theta SST model. If so could you please tell me where I'm going wrong and please suggests a way to solve this problem.
Any help on this matter is greatly appreciated.
Thanks in advance :)
Attachment 7360, Attachment 7361
Attachment 7362, Attachment 7364
Looks like you problem is more to do with this FAQ:
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