I'm working on transonic validations of a 2 d Nozzle design for a supersonic cruise. But my results are not matching with experimental data ( Pressure coefficient Vs Position) . Can anyone help me in correcting my boundary conditions. ?
for free stream mach 1.2, and reference pressure 35710, how much should be the supersonic static pressure for stagnation inlet and pressure for pressure outlet.
Thanks in advance.!!
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