Airfoil simulation in High Angles of Attack
Hello everyone: Recently I have done a research about the simulation of an airfoil in high angles of attack. Surprisingly, I figured out when I use a first order discretization scheme instead of a second order one for all the equations (flow equiations and turbulence kinetic energy and dissipation) I get much better results. It might be interesting to know that for example for an angle of attack of 60 degrees the predicted drag is about 5% off which is really great. I tried different angles as well to make sure that this does not happen accidently and all the results I've got for high angles are great. The results for low angles are very inaccurate though.
I was wondering if somebody has any idea about these phenomena?
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