[jaydarji395]

Hey guys,
I am trying to simulate NACA 0012 airfoil to learn and to get correct results for validation. I have created my mesh in blockMeshDict with 12 blocks which consists of 6 outer and 6 inner blocks. Well, I tried to simulate at AoA= 4 degree with y+=0.05. The input data is: Re=1e06, U=14.60734694 m/s, nu= 1.460734694e-05 m²/s, rho = 1.225 kg/m³. I am getting this weird wake region where the velocity, pressure and turbulence parameters are discontinuous, as can be seen from the figure. I have attached the boundary conditions and I am using pisoFoam algorithm to solve it. My assumption is that the 1st cell height being too small of the order 1e-06, and time step being 1e-05, I am getting this. The max Co= 45 nearly. I will post Co field as well.

My questions are: 1) Should I use this small cell height with kOmegaSST model?
2) I have also tried to use y+=1.5, i.e. 5e-05m height of first cell, and ran the simulation for AoA=4 degree. For this the maxCo at the end is 0.112129.
I get the Cd and Cl values 2.202755e-02, 3.365725e-01 respectively. These results do not agree with say Ladson or Xfoil results which are: 0.00728, 0.4276. What should I do to improve or to correct the results?

The coefficients I got with y+=0.05 were fluctuating, because of the reason I have described above.