Related Questions

The maximum propulsion efficiency of a turbojet is attained at around following speed
A 550 km/hr
B 1050 km/hr
C 1700 km/hr
D 2400 km/hr
The turbine of the turboprop engine is __________ that of the turbojet engine.
A Same as
B Smaller than
C Bigger than
D None of these
The power available for takeoff and climb in case of turbojet engine as compared to reciprocating engine is
A Less
B More
C Same
D May be less or more depending on ambient conditions
In turbo fan engine, the jet velocity as compared to turbojet engine is
A Less
B More
C Same
D May be less or more depending upon speed
A simple turbojet engine is basically
A A propeller system
B Gas turbine engine equipped with a propulsive nozzle and diffuse
C Chemical rocket engine
D Ramjet engine
Propulsive efficiency is defined as ratio of
A Thrust power and fuel energy
B Engine output and propulsive power
C Propulsive power and fuel input
D Thrust power and propulsive power
In open cycle turbojet engines used in military aircraft, reheating the exhaust gas from the turbine by burning, more fuel is used to increase the
A Thrust and range of aircraft
B Efficiency of the engine
C Both (A) and (B)
D None of these
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
Which of the following fuels can be used in turbojet engines?
A Liquid hydrogen
B High speed diesel oil
C Kerosene
D Methyl alcohol
Ram compression in turbojet involves
A Reduction of speed of incoming air and conversion of part of it into pressure energy
B Compression of inlet air
C Increasing speed of incoming air
D Lost work

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