[jonny_b]

I have run an axisymmetric simulation of a convergent-divergent nozzle with external flow in Star-CCM. I would like to extract the nozzle thrust and drag and the nacelle drag. I am trying to calculate these values at the nozzle exit plane, consistent with how I would do this for a structured mesh. I have one continuous region and would like to create a derived plane part at the nozzle exit, but from my initial meddling, it seems that this type of plane is not possible for 2D meshes.

Has anybody tried to extract thrust info out of an axi mesh from Star-CCM and would like to share their wisdom?

Thanks,

Jonathan