Boundaries, nacaAirfoil Case - Compressible, sonicFoam, RAS
 

Hi there,

I'm trying to run a supersonic simulation of a NACA airfoil. I have made and tested the airfoil mesh in other simpler solvers and now I want to implement it in the tutorial case called nacaAirfoil for sonicFoam.

I wanted to try this particular case previously to know a little bit more about it but, apparently, it does not contain any mesh. So I want to implement mine in it. I guessed that the process should be to try to fit my boundaries with the ones that the case originally has.

The problem is that there are a lot of initial files inside 0 folder and they have a struture like this: (this precise one is for pressure)

boundaryField
{

"inlet.*"
{
type zeroGradient;
}

"outlet.*"
{
type waveTransmissive;
field p;
psi thermo: psi;
gamma 1.4;
fieldInf $pressure;
lInf 1;
value $internalField;
}

"sym.*"
{
type empty;
}

"wall.*"
{
type zeroGradient;
}

}

My geometry is a thin cuboid with the airfoil inside (type wall), front and back (type empty) and inlet, outlet, top, bottom (type patch). As the case is written with .* I guess that it could have different intlets, outlets, etc...

Any clue on how I could relate all this with the mesh that I have? Should it work if I just simple rename my boundaries or those in the case to fit together?

Thanks!

Hello Jarufe.

I'm currently using the sonicFoam solver to simulate the supersonic flow over a Busemann (or diamond or biconvex) arifoil. I used the "prism" tutorial, but it is similar to your case.

About your question:
I also want to know what the ".*" means. However, I think that if you remove the ".*" and simply match the boundary names, it will work. Have you tried this already?