2D Airfoil modeling using Spalart Allmaras Model
I am trying to find lift and drag coefficient of NACA2412 airfoil using Spalart Allmaras (SA) Model for Reynolds number 10^6. But the solution is not converging and calculated Cd and Cl values are far from actual one. I have checked y+ value in between 1~28.
Can anyone suggest me about improving convergence criteria for SA model? or Any reading material related to using SA model in fluent? Is there any special tricks on meshing? or How I can modify mesh in fluent to improve convergence? Thank you in advance. Waiting for reply. 
y+ from 1 to 28 means your grid is bad. For Spalart Allmaras you need to keep your y+ less then 1 OR larger then 100. Using a grid with y+ from 1 to 100 will give you a bad solution.
Do 
Thank you DoHander.
Can you suggest me any procedure by which I can reduce y+ closer to 1. I will be highly grateful for this help. 
You can estimate the height of the first row of cells at the wall imposing an y+ of say 100 and providing the Mach and Reynolds numbers for your case. You have an y+ calculator here in cfdonline from which you can estimate what is the minimum cell height at the wall.
Do 
Thank you DoHander. I have tried with the calculator to calculate the cell height. Not yet successful.
Probably I have to take more care about mesh formation. If you have any 2D airfoil mesh you may share with me. That will be a great help. 

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