[andimb]

Hi!

I'm still calculating a flow around a NACA airfoil and compare it to a CFX solution.
I use the LaunderSharmaKE turbulence model with an yplus near 1.
If I start a calculation with the same boundary condiations as in CFX, where epsilon is calculated by epsilon = density*C_mu*k^2/eta_T and eta_T=10*eta where eta is the dynamic viscoity, the solver reaches no steady solution, seen in the first image.

If I use the following formulationfor epsilon: epsilon = k^(3/2)/L with L as an charactersitic length as the chordlength, I get a much lower epsilon and the solution is steady but with a too big boundary layer ass seen in the picture.


I also try other turbulence models and guessed epsilons and finer or coarser meshes, with no dramatic change.

I don't see the mistake I make.

Thanks for help!
Andreas