Rocket Propulsion MCQs : This section focuses on the "Rocket Propulsion". These Multiple Choice Questions (MCQs) should be practiced to improve the Rocket Propulsion skills required for various interviews (campus interview, walk-in interview, company interview), placement, entrance exam and other competitive examinations.
Question 1
Which of the following is not an air-breathing engine?
A. Turbojet
B. Turbofan
C. Rocket
D. Scramjet
Question 2
Which of the following is not a valid classification of rocket engines based on their energy source?
A. Chemical
B. Geothermal
C. Solar
D. Nuclear
Question 3
What is the range of temperature of reaction product gases in a rocket engine?
A. 500 to 1700 °C
B. 1700 to 2500 °C
C. 2500 to 4100 °C
D. 4100 to 6900 °C
Question 4
What is the typical liquid propellant feed system used in space launch vehicles?
A. The Gas pressure feed system
B. Pump-fed system
C. Gravity assisted feed system
D. No feed system is used
Question 5
For a constant thrust of 6000 N, find the total impulse for the burning time of 3s.
A. 36000 Ns
B. 18000 Ns
C. 9000 Ns
D. 0 Ns
Question 6
For an ideal rocket, what should be the nature of the working substance?
A. Homogeneous
B. Heterogeneous
C. Anisotropic
D. Amorphous
Question 7
Which of the following statements is correct for an ideal rocket?
A. All kinds of frictional effects are not present, but the boundary layer cannot be neglected
B. All discontinuities are not present, but shock waves are allowable
C. Propellant flow is steady but constant
D. The expansion of the working fluid is steady, but need not be uniform
Question 8
Select the correct option for an ideal rocket engine.
A. The exhaust gases leaving the rocket need not be axially directed
B. Across any cross-section normal to the nozzle axis, gas velocity need not be uniform
C. The gas composition can vary across the nozzle
D. Cryogenic propellants need to be stored at their boiling points
Question 9
Which of the following relations won’t hold in an ideal rocket engine’s nozzle?
A. Isentropic expansion relations
B. Conductive heat transfer relations
C. Homogeneous flow relations
D. Ideal gas law relations
Question 10
__________ is not liquid fuel.
A. Xylidine
B. Furfuryl alcohol
C. Hydrazine hydrate
D. Nitric acid
Question 11
Consider two rocket engines A and B with A having a specific impulse of 242s and B having a specific impulse of 150s. What can be said about their efficiency?
A. Both A and B are equally efficient
B. A is more efficient than B
C. B is more efficient than A
D. Efficiency doesn’t depend on specific impulse
Question 12
For a rocket, the specific impulse was found to be 250s. Given that the thrust force is constant and assuming gravity-free and drag-free conditions, what will the thrust force be for a mass flow rate of the form (4t2-3t) kg/s and a burn duration of 3s?
A. 18375 N
B. 12426 N
C. 25234 N
D. 15595 N
Question 13
Given that the total impulse is 25000 Ns and specific impulse is 300s, find out the effective propellant mass for a burn duration of 8s.
A. 17 kg
B. 8.5 kg
C. 34 kg
D. 68 kg
Question 14
Suppose the thrust force of a rocket varies with time t as F = 250(3t2 + 2t). Then find out the total impulse for a burn duration of 4s.
A. 10000 Ns
B. 20000 Ns
C. 40000 Ns
D. 80000 Ns
Question 15
Which of the following pressure feed systems is mostly used in attitude control of liquid propellant rocket engine with more than one thrust chamber per engine?
A. The Gas pressure feed system
B. Pump-fed system
C. Gravity assisted feed system
D. No feed system is used