[alvarrapi9]

Hi to everyone,

I have a 2D axysmetrical thruster simulation, internal, steady and laminar with compressible flow and energy equation. The point is that after establishing a pressure-inlet condition in which I fixed the gauge pressure and the temperature I get a converged solution (low and stable residuals and stable variables (I plot different averages and all of them are stabilised) but the problem is that even the solution seems to be really converged the inlet values are not the one I input.

For example, depending on the geometry I get values between 630K-655K on temperature but not the 673,15K that I fixed (same with the pressure). I do not think there are any problems with the mesh as long as I have previously done a grid independent study and the results were fine. I would really appreciate some guides about what can be going on as I have tried a lot of things but the solution still not reach the values I have established at the inlet even it is converged.

Thank you!

[LoGaL]

Which values are you extracting from the simulation? Static Temperature and Pressure? Just to tell you that your boundary conditions impose the total ones

[alvarrapi9]

Originally Posted by LoGaL

Which values are you extracting from the simulation? Static Temperature and Pressure? Just to tell you that your boundary conditions impose the total ones

Thank you for the answer! I am extracting the static values. However, I consider that the pressure and temperature are the total values so I input these values in the boundary conditions calculating them with the same procedure that Fluent does (Cp constant and compressible flow). The problem is that I am not reaching the static values and If I change the geometry even the boundary conditions are the same the reached values changes again...