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

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

ANSWER DOWNLOAD EXAMIANS APP

Compressors, Gas Turbines and Jet Engines
The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the

Stator to static enthalpy rise in the stage
Rotor to static enthalpy rise in the stage
Rotor to static enthalpy rise in the stator
Stator to static enthalpy rise in the rotor

ANSWER DOWNLOAD EXAMIANS APP