Vroticess not appearing in motor combustion flow
I am simulating burning of a segmented rocket motor C1xb. The steady simulations should have vortices appearing in the flow. While I tried both steady and then transient simulations I do not get any vortices. I dont know why. My boundary conditions are Mass flux inlet. Nozzle exit as pressure outlet, ilet pressure is 12 bar and wall boundary conditions.
What pressure should I put at pressure outlet? Atmos. pressure or calculated pexit and then put this in pr outlet.
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