Issue with transition models
5 Attachment(s)
Hi guys,
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 Attachment 7365 |
Looks like you problem is more to do with this FAQ:
http://www.cfd-online.com/Wiki/Ansys...gence_criteria |
All times are GMT -4. The time now is 04:37. |