[Springyuu]

Hi, I'm doing a simulation that the air of 0.28 MPa flow into a tank of 100 Pa. There is a supersonic flow during the air flow. I choose the supersonic flow regime for the inlet boundary, and set the static pressure to 100 Pa and total pressure to 0.28 MPa due to the velocity is unknown.
however, I found that when the static pressure is 100 Pa, 200 Pa and other different values, the calculated mass flow rate on the inlet surface is different, respectively 0.0021 kg/s, 0.0034 kg/s, which are not in accordance with a formula. I also try to set the static pressure 0.28 MPa, but there is an error occurred that fatal overflow in linear solver.
So I wonder how should I set the static pressure and total pressure. if the static pressure should be set to 0.28 MPa, how to adjusting the settings. I will be very grateful if you can provide any suggestions. Thanks a lot!

[ghorrocks]

Before you start drawing conclusions about your results, have you confirmed you have reduced numerical errors sufficiently that the results are meaningful?

See FAQ: https://www.cfd-online.com/Wiki/Ansy..._inaccurate.3F