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Station 5: end of turbine

Actual turbine work extracted = fan work + compressor work

From this, the actual pressure can be found from the isentropic relation.

Station 6: end of afterburner

Afterburner is OFF, and we'll assume that there are no losses in the duct:

Station 7: exit of hot nozzle:


Assume that the nozzle exit pressure is the same as the ambient pressure:

The exit temperature can be found using the isentropic relation:

Exit Mach number is

Hot exit velocity is:

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