my analysis is for supersonic case, my Pc = 6.895e+6Pa and Tc = 2777.778 K and Pa and Ta for ground ambient conditions.
Does that means for supersonic rocket nozzle analysis, the boundary conditions which I have used, are correct and I only need to focus on Mesh around jet due to presence of shocks or expansion waves ?
Can you please confirm this, If boundary conditions are correct then I think I don't have to worry about that part for the least. So that I can focus more on meshing around jet, as making structured mesh is becoming difficult due to slanted part of nozzle.
Does that means for supersonic rocket nozzle analysis, the boundary conditions which I have used, are correct and I only need to focus on Mesh around jet due to presence of shocks or expansion waves ?
Can you please confirm this, If boundary conditions are correct then I think I don't have to worry about that part for the least. So that I can focus more on meshing around jet, as making structured mesh is becoming difficult due to slanted part of nozzle.
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