[Martin007]

Hello everyone,

I'm learning CFD with Ansys. I would like to simulate condensation which is appearing when a jet fighter is at a transonic/sonic speed. For the moment I test my settings on a bullet geometry.

Here are my settings :
density based

Model :
Wet Steam
Energy-ON
Turbulent : k-epsilon

Boundary conditions
Pressure inlet : 101325 Pa
Supersonic/ initialisation pressure : 54752 Pa
T=300K

Pressure Outlet : 54752 Pa
T=300K

I expected to see condensation just after my geometry, however, as you can see on the picture the liquid fraction is constant almost everywhere and equal to 0.1. Could you explain me where is my mistake ?

Thank you in advance for your answer.
Sincerely,
Martin David