[aero_cfd]

Hi,

i am investigating an a 10 deg flapped airfoil, Re=6.75e5 , Mach=0.1 , y+<1 . using the K-omega SST turbulence model, pressure based solver with SIMPLE algorithm,2nd order schemes. in order to get the right Re number I changed in the viscosity which is 6.174e-05 , the velocity is about 34 m/s.

The issue I am having is that after running at post stall angles of attack, I don't have vortex shedding, the Cl max angle is 13 , when I run 14 and 15 i get convergence with the steady state but no shedding, 16 and 17 I don't get the convergence in steady state but it doesn't diverge , so when i start the unsteady solver i start with the unconverged steady results, which gives some highly turbulent flow with vortex shedding , but how much can these results be trusted ?

What may be the cause of not having the vortex shedding ?

Thank you !