Best practices for performing an analysis on a supersonic C-D nozzle in Star-CCM
I am having a bit of difficulty creating an appropriate mesh and initializing my solution such that my CFD solution does not diverge (I am getting floating point exceptions after about 15 iterations).
Can anybody point me to a set of best practices to use for running CFD on C-D nozzles in Star-CCM
Assuming you are using the Coupled Solver, you should try AUSM+ for the Coupled Inviscid flux option and Grid Sequencing for the initialisation, then ramp your CFL.
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