Aerospace Engineering > GATE 2014 > Engine Performance
For a given fuel flow rate and thermal efficiency, the take-off thrust for a gas turbine engine burning aviation turbine fuel (considering fuel-air ratiof<<1) is
A
Directly proportional to exhaust velocity
B
Inversely proportional to exhaust velocity
C
Independent of exhaust velocity
D
Directly proportional to the square of the exhaust velocity

Correct : b

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