|March 12, 2005, 05:24||
how to model supersonic reacting flows
1)which solver is suitable for compressible,steady state,supersonic reacting flows in rocket thrust chamber.
2)how can i calculate the length and diameter of conevrging and diverging nozzle for particular area ratio.
3)i modeled the nozzle but the flow is not following nozle walls and the results are not acceptable.
4)could you mension which type of boundary conditions applicable for rocket thrust chamber.
i hope you can clear my doubts
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