[klausb]

Hello,

I try to reproduce an airfoil simulation at Re = 1.000.000 which has originally also been done using OpenFoam komegaSST.

Expected vs. achieved cl/cd results are:

expected cl: 1.1401 >> my own result 1.0574 (experiment/wind tunnel = 1.1320)

expected cd: 0,0225 >> my own result 0.0223 (experiment/wind tunnel = 0.0121)

Of course cd is not predicted correctly as komegaSST assumes full turbulence whereas this is a case of transitional flow laminar > turbulent so using kklomega will be the next step. Nevertheless at the moment I am trying to reproduce the results of the komegaSST simulation using the same model.


I have been playing with the mesh but cl remains at 1.05x.

The only known factor I haven't been using is the turbulent intensity of Tu = 0.06%.

What factor could have such an impact on cl?

Klaus