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

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

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Compressors, Gas Turbines and Jet Engines
The overall isothermal efficiency of the compressor is defined as the ratio of

Volume of free air delivery per stroke to the swept volume of the piston
Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor
Isentropic power to the power required to drive the compressor
Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio

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