ExamVeda
Login
Home

Which of the following statement is correct relating to rocket engines...

This question belongs to Mechanical Engineering Compressors, Gas Turbines And Jet Engines
Compressors, Gas Turbines and Jet Engines
?

Which of the following statement is correct relating to rocket engines?

Answer & Solution
Correct Answer: Option D
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel - The stagnation conditions exist at the combustion chamber -The exit velocities of exhaust gases are much higher than those in jet engine
Examveda
Question posted by Examveda
Community

Join the Discussion

No comments yet Be the first to discuss this question.
Keep Learning

Related Questions on Compressors, Gas Turbines and Jet Engines

The compression ratio for the compressor is always _________ unity.
A. Equal to B. Less than C. More than D. None of these
The hottest point in a gas turbine is
A. At the base B. At the tip C. In the center D. Between ~ to i of the blade height
Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is
A. Higher B. Lower C. Equal D. Can't be compared
The maximum temperature in a gas turbine is
A. 200°C B. 500°C C. 700°C D. 1000°C
More Related Questions on Compressors, Gas Turbines and Jet Engines