[ColourAshRed]

Hello everyone!

I am simulating a NACA0012 airfoil, from 0 to 180 degrees, and comparing the cl and cd results with NASA's experimental results. Up to stall, the Spalart-Allmaras model works just fine.

However, I am unable to get converging results using the k-epsilon model even at low angles of attack even after 20k iterations. I have set the y-plus value to 30, my Reynolds number is 700k. I will be attaching my 0/ and system/ files. Can someone please take a look and tell me where I've gone wrong or what I'm missing?

I have tried various things but I'm unable to set this right. I also want to know how to access the damping functions setting for the k-epsilon model in order to perform simulations for y-plus between 1&5.

If someone can also direct me on any resource on how to use the k-omega and k-omega SST models for separated flow over airfoils, it would be very generous and would help me a lot. I'm new to CFD on OpenFOAM, and this is my first project.

Thanks in advance!