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A converging diverging nozzle is connected to a gas pipeline.
At the inlet of the nozzle (converging section) the Mach number is
2. Itis observed that there is a shock in the diverging section.
What is thevalue of the Mach number at the throat?
At the inlet of the nozzle (converging section) the Mach number is
2. Itis observed that there is a shock in the diverging section.
What is thevalue of the Mach number at the throat?
- a)< 1
- b)Equal to 1
- c)> 1
- d)≥1
Correct answer is option 'B'. Can you explain this answer?
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A converging diverging nozzle is connected to a gas pipeline.At the in...
Ans. (b)
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A converging diverging nozzle is connected to a gas pipeline.At the in...
Explanation:
In a converging-diverging nozzle, the converging section of the nozzle is designed to accelerate the flow and increase the velocity of the gas. The diverging section of the nozzle is designed to decelerate the flow and increase the pressure of the gas.
In this case, the Mach number at the inlet of the nozzle is given as 2. The Mach number is defined as the ratio of the velocity of the gas to the speed of sound in the gas. A Mach number greater than 1 indicates that the gas is supersonic.
When the supersonic flow passes through a converging-diverging nozzle, it undergoes a series of compressions and expansions due to the changes in the nozzle geometry. These changes can lead to the formation of shocks in the flow.
Shock in the diverging section:
The presence of a shock in the diverging section of the nozzle indicates that the flow has undergone an expansion and is now subsonic. A shock wave is a discontinuity in the flow where the flow properties change abruptly.
Mach number at the throat:
The throat of the nozzle is the narrowest section where the flow velocity is maximum. At the throat, the flow velocity is equal to the speed of sound in the gas. Therefore, the Mach number at the throat is equal to 1.
Conclusion:
In this case, since there is a shock in the diverging section of the nozzle, the Mach number at the throat is equal to 1. Therefore, the correct answer is option 'B' - Equal to 1.
In a converging-diverging nozzle, the converging section of the nozzle is designed to accelerate the flow and increase the velocity of the gas. The diverging section of the nozzle is designed to decelerate the flow and increase the pressure of the gas.
In this case, the Mach number at the inlet of the nozzle is given as 2. The Mach number is defined as the ratio of the velocity of the gas to the speed of sound in the gas. A Mach number greater than 1 indicates that the gas is supersonic.
When the supersonic flow passes through a converging-diverging nozzle, it undergoes a series of compressions and expansions due to the changes in the nozzle geometry. These changes can lead to the formation of shocks in the flow.
Shock in the diverging section:
The presence of a shock in the diverging section of the nozzle indicates that the flow has undergone an expansion and is now subsonic. A shock wave is a discontinuity in the flow where the flow properties change abruptly.
Mach number at the throat:
The throat of the nozzle is the narrowest section where the flow velocity is maximum. At the throat, the flow velocity is equal to the speed of sound in the gas. Therefore, the Mach number at the throat is equal to 1.
Conclusion:
In this case, since there is a shock in the diverging section of the nozzle, the Mach number at the throat is equal to 1. Therefore, the correct answer is option 'B' - Equal to 1.
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A converging diverging nozzle is connected to a gas pipeline.At the inlet of the nozzle (converging section) the Mach number is2. Itis observed that there is a shock in the diverging section.What is thevalue of the Mach number at the throat?a)< 1b)Equal to 1c)> 1d)≥1Correct answer is option 'B'. Can you explain this answer?
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