Compressors, Gas Turbines and Jet Engines
Which of the following statement is correct relating to rocket engines?

The exit velocities of exhaust gases are much higher than those in jet engine
All of these
The stagnation conditions exist at the combustion chamber
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel

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Compressors, Gas Turbines and Jet Engines
The specific output per kg mass flow rate of a gas turbine (having fixed efficiencies of compressor and turbine and fixed higher and lower temperature) with increase in pressure ratio will

Increase first at fast rate and then slow
Increase first at slow rate and then fast
First increase, reach maximum and then decrease
Decrease continuously

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