[tareqkh]

Hey Foamrs,

In fact, I have run the airfoil example that is provided with simpleFoam. As many if you might be aware, the example already comes with Spalart Allmaras turbulence model. The 0 folder consists of nut and nuTilda, so I have tried to calculate the boundary conditions that are already provided, which are 0.14 for both nut and nuTilda. I have used the equations on CFD wiki, but I am unable to get the 0.14. So far, I have seen many comments about it on the forum, but they are not sufficient. I would be really thankful if you guys explain how can I get it or explain how it is there?

Free stream velocity= 26m/s.
nu=1e-05 m2/s.
rho=1 kg/m3.

nut=nuTilda=0.14 <-------------- This weird value.

Kind regards,