[Jefferson_dhv]

I'm trying to simulate a NACA 0012 in transonic conditions to have a initial set up that I can further modify to run other airfoils in the same conditions.

I'm really in the beginning with OpenFOAM so at first I was in doubt about the solver to use, so reading some threads in the forum I saw that sonicFoam and rhoCentralFoam would be the best for a case like this.

As the simulation takes a lot of time to get to the steady state it's been hard to change parameters and identify by myself the problem, that is the non convergence of the case. So I would like some tips to achieve the convergence in my case and to help reducing the computational time required. For me it's been hard to find information about compressible solvers, so any resource provided would be helpful too.

Monitoring the results I could see that the value of CD was increasing and the value of CL was decreasing indefinitely.

The simulation was with 4 degrees aoa.

Here follows my set up

Mesh1
Mesh2

checkMesh

/0
alphat
epsilon
k
mut
P
T
U

/system
controlDict
fvSchemes
fvSolution


Thanks in advance,
Jefferson Vieira