- #1
nakas12
- 12
- 0
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?
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 each other where:
A1/A* = A2/A*
A* = Throat area
Looking at the isentropic flow table I would assume both mach number equal to each other.
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 each other where:
A1/A* = A2/A*
A* = Throat area
Looking at the isentropic flow table I would assume both mach number equal to each other.