[UsamaQ]

Hello,

I am trying to simulate the heat transfer between the jet vane and the flow at the exit of nozzle. I have setup pressure inlet and outlet and have both solid (jet vane made of steel) and fluid (air) domains. I simulated the steady state solution using explicit 1st order upwind scheme and found a good match between CFD and experimental thrust data. Other values are also matching except temperature of the jet vane.

Now the problem is that when I initialize the solution from inlet @3275 K, the whole domain is set to 3275 K which eventually converges to accurate value but the temperature of the vane keeps increasing and stays between 3300-3700K which is really absurd as the flow at the nozzle exit is around 1100K. I tried to re simulate using standard initialization again at nozzle inlet but with temperature of 300K (instead of 3275 K), but this results in divergence. I tried to lower courant number and relaxation factors but couldn't succeed.
The thermal boundary condition at vane walls is coupled.
I need your help for this! Can I set up the initial jet vane temperature at 300K?

Thank you!