Reply To: Set up the flow solver

[Aras karimi]

Federico, I raised the issue of non-validation of my CFD results with experimental results in the topic (/forum/forums/topic/validation-of-airfoil-lift-and-drag-coefficients/#post-319795).

My mesh has good resolution and quality and its Y+ is below one. I used the K-Omega SST model and obtained its performance curve up to 10° angle of attack, which is as shown below:

 

I ran all simulations from 0° to 10° angle of attack as steady state and the residuals went down to 1e-13 and the CL and CD graphs were smooth. According to the picture above, there is a huge difference in the results. Because the Reynolds flow is in the transition region, I want to use the SST transition turbulence model.

Federico I have been involved in the validation of my results for a very long time and I suffer from this issue.

Please help me

Regards