A turboprop is preferred to turbojet because
A. It has high propulsive efficiency at high speeds
B. It can fly at supersonic speeds
C. It can fly at high elevations
D. It has high power for take off
Answer: Option D
A. It has high propulsive efficiency at high speeds
B. It can fly at supersonic speeds
C. It can fly at high elevations
D. It has high power for take off
Answer: Option D
The compression ratio for the compressor is always _________ unity.
A. Equal to
B. Less than
C. More than
D. None of these
The hottest point in a gas turbine is
A. At the base
B. At the tip
C. In the center
D. Between ~ to i of the blade height
Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is
A. Higher
B. Lower
C. Equal
D. Can't be compared
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