Comparing Experimental and Computational results.
I am trying to compare experimental results of a Mach 2 jet with nozzle pressure ratio(NPR) = 1.2 with the computational results , my problem is : 1) Say the freestream Mach number is 0.05 what values of pressure, temperature do I use in order to initialise the computational flow field? 2) Given the jet exit conditions (M=2 and NPR=1.2) how can I calculate the static temperature and static pressure values ?
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