[MikePo]

Dear Foamers,

I am trying to evaluate the performance of the sonicFoam solver when applied to a transonic aerofoil case (RAE2822). Using a reasonably fine mesh with the k-epsilon turbulence model I have obtained the attached result (compared with experimental data). The free stream Mach number is 0.75, alpha=2.81, Re=6.5e6.

As you can see, the pressure distribution shows good correlation to the experimental data, however the shock is quite far downstream. Is this a problem with the turbulence model I have used? If so, has anyone any advice on a more suitable model to apply to this problem??


Michael