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Old   July 2, 2008, 09:51
Default Mach number
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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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