Question: A simple turbojet is operating with a compressor pressure ratio of 1 6 . 0 , a turbine inlet temperature of 1 5 0 0

A simple turbojet is operating with a compressor pressure ratio of 16.0, a turbine inlet
temperature of 1500K and a mass flow of 15kgs, when the aircraft is flying at 260ms at an
altitude of 7000m. Assuming the following component efficiencies, and ISA conditions, calculate
the propelling nozzle area required, the net thrust developed and the SFC:
 A simple turbojet is operating with a compressor pressure ratio of

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