[Stefandres]

Hello,



I am trying to model a regeneratively cooled rocket nozzle. I have some empirical data for the modeled nozzle which states that heat flux through the nozzle wall should be between 2500 to max 20000 W/m^2 at the throat.



However so far I always get heat fluxes between 16000 to 45000 W/m^2 which is way too high. Due to this, the wall temperature also gets too high (up to over 1000K while it should be around 650K max). Pressure and velocity values match to empirical data, only the temperature and heat flux is off afaik.



Is it maybe a problem with the mesh? I'm using the k-omega SST model.


Any feedback is highly appriciated.


Regards
Stefan

[vinerm]

It depends on material properties, Re number, and the boundary condition you have on the wall. Look at the material properties that define Pr and Re. And then check the boundary condition you have applied on the wall.