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Consider the following statements relating to rocket engines:
1. The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel.
2. Stagnation conditions exist at the combustion chamber.
3. The exit velocities of exhaust gases are much higher than those in jet engines.
4. Efficiency of rocket engines is higher than that of jet engines.
Of these correct statements are
1. The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel.
2. Stagnation conditions exist at the combustion chamber.
3. The exit velocities of exhaust gases are much higher than those in jet engines.
4. Efficiency of rocket engines is higher than that of jet engines.
Of these correct statements are
- a)1, 3 and 4
- b)2, 3 and 4
- c)1, 2 and 3
- d)1, 2 and 4
Correct answer is option 'C'. Can you explain this answer?
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Consider the following statements relating to rocket engines:1. The co...
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The Correct Statements
The correct statements among the given options are:
- The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel. (Statement 1)
- Stagnation conditions exist at the combustion chamber. (Statement 2)
- The exit velocities of exhaust gases are much higher than those in jet engines. (Statement 3)
Explanation
Let's discuss each statement in detail:
Statement 1: The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel.
This statement is correct. In a rocket engine, the combustion chamber is where the fuel and oxidizer are mixed and burned to produce high-pressure and high-temperature gases. These gases then expand through a nozzle, generating thrust. Similarly, in a supersonic wind tunnel, the reservoir is where the high-pressure air is stored before it is released through a convergent-divergent nozzle. Both the combustion chamber in a rocket engine and the reservoir in a supersonic wind tunnel play a crucial role in generating high-speed flow.
Statement 2: Stagnation conditions exist at the combustion chamber.
This statement is correct. Stagnation conditions refer to the conditions at the "stagnation point" of a flow, which is the point where the flow velocity becomes zero. In the combustion chamber of a rocket engine, the flow velocity is very high due to the combustion process. However, at the stagnation point within the combustion chamber, the flow velocity becomes zero, and the pressure and temperature are at their maximum. These stagnation conditions are important for efficient combustion and high thrust generation.
Statement 3: The exit velocities of exhaust gases are much higher than those in jet engines.
This statement is correct. Rocket engines are specifically designed to achieve very high exit velocities of exhaust gases. The principle behind rocket propulsion is Newton's third law of motion, which states that for every action, there is an equal and opposite reaction. The high-pressure and high-temperature gases produced in the combustion chamber are expelled at high speeds through the rocket nozzle, resulting in a high exhaust velocity. In contrast, jet engines used in aircraft typically have lower exhaust velocities compared to rocket engines.
Statement 4: Efficiency of rocket engines is higher than that of jet engines.
This statement is incorrect. Rocket engines are generally less efficient than jet engines. The efficiency of an engine is determined by its specific impulse, which is a measure of how effectively the engine converts propellant mass into thrust. While rocket engines have high specific impulses compared to jet engines, they typically have lower overall efficiencies. This is because rocket engines carry both the fuel and oxidizer onboard, resulting in a higher propellant mass compared to jet engines, which only carry fuel and rely on atmospheric oxygen for combustion.
Therefore, the correct statements among the given options are 1, 2, and 3. Option C is the correct answer.
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Consider the following statements relating to rocket engines:1. The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel.2. Stagnation conditions exist at the combustion chamber.3. The exit velocities of exhaust gases are much higher than those in jet engines.4. Efficiency of rocket engines is higher than that of jet engines.Of these correct statements area)1, 3 and 4b)2, 3 and 4c)1, 2 and 3d)1, 2 and 4Correct answer is option 'C'. Can you explain this answer?
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