[nucat]

Hey,

I have to do some CFD work for my study. Please help me, I have to simulate supersonic flow around a 15° wedge. So I decided to take the rhoCentralFoam solver and the tutorial case forwardStep. I run that case and got plausible result. Than I adapt that case to my geometry and got no shock waves and no plausible result. My M_inf is 3 mach.

1. question:
how to treat walls? I defined in blockMeshDict the wall as "wall" and in 0/U I set there the velocity to zero.

2. question:
how to treat outflow? I used the default settings from forwardStep tutorial.

Please help me.

Greeting,
Daniel

[nucat]

For a better illustration here is an image of the pressure field. The mach number is 3, but there are no shock waves? I took the naca airfoil example for the sonicfoam and adapt that geometry and run a calculation with sonicFoam, the result was the same