Sonic velocity at the throat of a convergent-divergent nozzle

In summary, the conversation discusses the release of a gaseous fluid through a convergent-divergent nozzle, which can reach supersonic velocity if there is a sufficient pressure difference. The question posed is whether the velocity at the throat will always remain sonic regardless of the inlet to throat ratio and divergent section geometry, and if there are any factors that can affect this. The person asking for guidance is seeking a yes or no answer, which they can also find through Google. The conversation also mentions a potential need for knowledge in compressible flow to understand this problem.
  • #1
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TL;DR Summary
Sufficiently pressurised compressible fluid is being released through a convergent-divergent nozzle. I want to know that whether irrespective of the geometry and inlet to throat ratio of the nozzle, do the velocity at the throat will always remain sonic?
Sufficiently pressurised (difference between inlet and release pressure is enough to create supersonic flow) gaseous fluid is being released through a convergent-divergent nozzle. And it's a known fact that if pressure difference is sufficient, a convergent-divergent nozzle can release gaseous fluid at supersonic velocity. I want to know that whether irrespective of the inlet to throat ratio and geometry of the divergent section, do the velocity at the throat will always remain sonic or it need some factors to keep the velocity sonic at the throat.
 
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  • #2
Have you done any work to try to work out this problem on your own? If you are only looking for a yes/no answer, then you could get that from Google.
 
  • #3
How? Kindly guide me.
 
  • #4
Have you ever taken a compressible flow course or are you otherwise familiar with compressible flow?
 

1. What is sonic velocity at the throat of a convergent-divergent nozzle?

The sonic velocity at the throat of a convergent-divergent nozzle is the speed of sound at which the gas flowing through the nozzle reaches its maximum velocity. This is also known as the critical velocity.

2. How is sonic velocity calculated at the throat of a convergent-divergent nozzle?

The sonic velocity at the throat of a convergent-divergent nozzle can be calculated using the equation: V = (kRT)^0.5, where V is the velocity, k is the specific heat ratio, R is the gas constant, and T is the temperature.

3. Why is sonic velocity important in a convergent-divergent nozzle?

Sonic velocity is important in a convergent-divergent nozzle because it determines the maximum velocity that the gas can reach, which in turn affects the thrust and efficiency of the nozzle.

4. What factors affect the sonic velocity at the throat of a convergent-divergent nozzle?

The sonic velocity at the throat of a convergent-divergent nozzle is affected by the specific heat ratio, temperature, and gas constant of the gas flowing through the nozzle. It is also influenced by the shape and design of the nozzle.

5. How does the sonic velocity change in a convergent-divergent nozzle?

In a convergent-divergent nozzle, the sonic velocity increases as the gas flows through the converging section and reaches its maximum at the throat. It then decreases as the gas expands in the diverging section of the nozzle.

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