Aerospace Engineering > GATE 2011 > Compressor Performance
The pressure ratio in any one stage of a jet engine compressor is limited by
A
entry stagnation temperature in that stage
B
entry Mach number in that stage
C
pressure gradient induced separation in that stage
D
mass flow rate in that stage

Correct : c

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Related Topics

GATE Aerospace Engineering 2011 GATE AE 2011 Q23 jet engine compressor compressor stage pressure ratio pressure gradient induced separation compressor pressure ratio limit aircraft propulsion

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