[fxzf]

Hi Foamers,

In my simulation, I have a jet flow which is similar with Aircraft engine outlet. So at this inlet patch, I set mass flow rate and totaltemperature boundary condtion.

Now the problem is after simulation, I got the following solutions at this flow inlet patch

T (static temperature) = 803 (this is satisfy what I expected)
rho = 0.4633 (this is satisfy what I expected)
U = 156.8 (this is satisfy what I expected)
p = 1.156e5

The problem is pressure p. If we perform a hand calculation using perfect gas state equation, p = rho*R*T = 0.4633 * 287.1 * 803 = 106809.78429 = 1.068e5 which is also what I expected value. However, the p I got from solution is 1.156e5. This is not what I expected and not even satisfy perfect gas state equation.

Doese anyone has any idea what is wrong here?

Thanks a lot.