IndiaBIX

Mechanical Engineering - Compressors, Gas Dynamics and Gas Turbines

Exercise : Compressors, Gas Dynamics and Gas Turbines - Section 2
41.
Which of the following statement is correct relating to rocket engines ?
The combustion chamber in a rocket engine is directly analogous to the reservoir of a super sonic wind tunnel
The stagnation conditions exist at the combustion chamber
The exit velocities of exhaust gases are much higher than those in jet engine
all of the above
Answer: Option
Explanation:
No answer description is available. Let's discuss.
42.
In reciprocating air compressors, isothermal efficiency is used for all sorts of calculations.
Correct
Incorrect
Answer: Option
Explanation:
No answer description is available. Let's discuss.
43.
Euler's equation can be used for
radial flow compressors
axial flow compressors
pumps
all of these
Answer: Option
Explanation:
No answer description is available. Let's discuss.
44.
A rocket engine uses __________ for the combustion of its fuel.
surrounding air
compressed atmospheric air
its own oxygen
none of these
Answer: Option
Explanation:
No answer description is available. Let's discuss.
45.
The perfect intercooling, in multistage compression, means that the temperature of air at inlet to subsequent stages is equal to the initial temperature.
Agree
Disagree
Answer: Option
Explanation:
No answer description is available. Let's discuss.
Quick links
Quantitative Aptitude
Verbal (English)
Reasoning
Programming
Interview
Placement Papers