Hey guys I was wondering if a symmetric C-D nozzle has the same area at the inlet and exit, can the mach numbers at both points be the same?(adsbygoogle = window.adsbygoogle || []).push({});

This situation would involve a normal shock which would be near the exit as well. I would assume the Mach number at the throat would be 1.

With that said in terms of area ratios between area 1 and 2 at the inlet and exit and the throat, that the ratios would be equal to eachother where:

A1/A* = A2/A*

A* = Throat area

Looking at the isentropic flow table I would assume both mach number equal to eachother.

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# Symmetric Converging-Diverging Nozzle Areas?

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