Aerospace Engineering > GATE 2020 > Compressor Aerodynamics
The ratio of exit stagnation pressure to inlet stagnation pressure across the rotating impeller of a centrifugal compressor, operating with a closed exit, is
A
0
B
1
C
>1
D
0.5

Correct : c

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centrifugal compressor stagnation pressure GATE Aerospace Engineering 2020 exit stagnation pressure inlet stagnation pressure closed exit compressor stagnation pressure ratio aerospace engineering gate compressor stagnation pressure

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