Rocket Nozzle with combined equilibrium/frozen flow

In summary, the conversation discusses using the NASA CEA code to generate Isp and thrust data for the SSME. The problem is solved twice, with frozen and equilibrium flow conditions. However, there is a request for solving the problem with a combination of both conditions, which was not covered in the lecture. The solution involves using the "rocket" problem type and tripping the "frozen" or "equilibrium" flag. The "frozen and equilibrium both" flag works the problem twice, but does not provide a solution for the combination of conditions. The individual is seeking help on how to proceed with this request.
  • #1
igowithit
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1

Homework Statement


I am using the NASA CEA code to generate Isp and thrust data for the SSME. I solve the problem twice, once with a frozen flow condition and a second time with an equilibrium flow condition.

However, there is a third request for solving the problem with equilibrium flow from the combustion chamber to the nozzle throat and frozen flow from the throat to the nozzle exit. This wasn't covered in lecture and I'm unsure of how to do this?

Homework Equations


None

The Attempt at a Solution


Solving the problem for frozen or equilibrium flow is simply inputting the data into CEA under a "rocket" problem type and the "frozen" or "equilibrium" flag tripped. There is a "frozen and equilibrium both" flag, but it simply works the problem twice the same way as if you had individually ran each case.

Any help? I don't know where to go.
 
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What is a rocket nozzle with combined equilibrium/frozen flow?

A rocket nozzle with combined equilibrium/frozen flow is a type of nozzle design used in rocket engines. It combines the principles of both equilibrium flow and frozen flow to optimize engine performance.

How does a rocket nozzle with combined equilibrium/frozen flow work?

This type of nozzle uses a combination of subsonic and supersonic flow to achieve maximum thrust. The nozzle has a converging section that accelerates the exhaust gases to supersonic speeds, followed by a diverging section that expands the gases to create thrust.

What are the advantages of using a rocket nozzle with combined equilibrium/frozen flow?

One advantage is that it allows for a wider range of operating conditions, making the engine more versatile. It also improves engine efficiency by reducing the amount of unburned fuel in the exhaust and increasing thrust.

Are there any limitations to using a rocket nozzle with combined equilibrium/frozen flow?

Yes, this type of nozzle design is more complex and expensive to manufacture compared to traditional nozzles. It also requires precise control of the flow conditions to achieve optimal performance.

Can a rocket nozzle with combined equilibrium/frozen flow be used in all types of rocket engines?

No, this type of nozzle design is typically used in liquid rocket engines, as they have the ability to control the flow conditions more accurately. Solid rocket engines generally use simpler nozzle designs.

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