Test: Jet & Rocket Propulsion System - 2


10 Questions MCQ Test Topicwise Question Bank for Mechanical Engineering | Test: Jet & Rocket Propulsion System - 2


Description
This mock test of Test: Jet & Rocket Propulsion System - 2 for Mechanical Engineering helps you for every Mechanical Engineering entrance exam. This contains 10 Multiple Choice Questions for Mechanical Engineering Test: Jet & Rocket Propulsion System - 2 (mcq) to study with solutions a complete question bank. The solved questions answers in this Test: Jet & Rocket Propulsion System - 2 quiz give you a good mix of easy questions and tough questions. Mechanical Engineering students definitely take this Test: Jet & Rocket Propulsion System - 2 exercise for a better result in the exam. You can find other Test: Jet & Rocket Propulsion System - 2 extra questions, long questions & short questions for Mechanical Engineering on EduRev as well by searching above.
QUESTION: 1

Propulsion efficiency is defined as the ratio of

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QUESTION: 2

For maximum overall efficiency of a turbojet engine, the aircraft velocity and the jet velocity conform to the ratio

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QUESTION: 3

The thrust augmentation of turbojet engine can be effected by the following methods except

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QUESTION: 4

The surrounding air is not used as oxidiser in

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One major difference between the rocket engine power plant and other jet propulsion systems is that the rocket carries its entire propellant (oxidiser and fuel) with it. Other jet propulsion systems depend upon atmospheric air.

QUESTION: 5

The propulsion system having highest efficiency at higher speed

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QUESTION: 6

Lowest thrust per unit engine weight is developed by

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QUESTION: 7

The power plant having highest specific fuel consumption

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QUESTION: 8

Which one of the following is the correct expression for the propulsion efficiency of a jet plane (neglecting the mass of fuel)?

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QUESTION: 9

The type of nozzle used in rocket propulsion system is

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QUESTION: 10

Thrust in a rocket depends on

Solution:

Thrust is given by

where,
m = Propellant flow rate
Cj = Exhaust velocity
Pn = Nozzle exhaust static pressure
Pa - Atmospheric pressure
Ae = Nozzle exhaust area