I am given the Chamber, jet exit and ambient conditions (pressure and temperature). I needed clarification on the definition of Mach number if Mj = sqrt ((2/(gamma -1)) *[(po/pa)^(gamma/gamma-1)-1])
Basically the Isentropic Mach number. How do I calculate the Mach number at the nozzle exit plane?
Secondly, I would appreciate it if anyone could please point out some references for sonic and supersonic nozzle profiles. I need the correct nozzle geometry data for grid generation.
Thanks a lot.
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