Aerospace Engineering > GATE 2018 > Gas Turbine Cycles
The stagnation pressures at the inlet and exit of a subsonic intake are 100 kPa and 98 kPa, respectively. The pressure recovery of this intake will be ________ (accurate to two decimal places).

Correct : 0.98 to 0.98

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stagnation pressure subsonic intake pressure recovery Aerospace Engineering GATE 2018 GATE AE 2018 Q24 intake pressure recovery fluid dynamics aerospace aerospace engineering fluid mechanics

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