I'm trying to simulate aerospike nozzle at sea level. From my calculation, I should get ~2.71 exit Mach number but I get reversed flow in pressure inlet. When I use Roe-FDS, I get reversed flow in inlet after several thousands iteration.
Even if I leave the calculation(never converged), the flow doesnt even look like I expect it to be. Not even close.
I can't seem to attach my files. The loading is too long. So I insert it to external download link from WeTransfer instead.
-Cp 1006.43 J/kg k
-Molecular weight constant 28.966 kg/kmol
-Gauge total pressure 1500000 Pa
-Supersonic gauge pressure 1499999 Pa
-Total temp 900 K
-Gauge pressure 101325
-Total temp 288 K
Flux type: AUSM
-Least squares cell based
-2nd order upwind
The rest is left at default.