convergency problem at mach 3
I have a problem related with convergency. I try to solve a missile geometry at Mach=3. It converges while using 1st order discretization but when I switch flow equation to 2nd order discretization, it diverges. I try to solve density based explicit and implicit, startted from lower mach number then I changed the mach number to 3 , however none of them work. Could anybody help me?
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