Rocket Nozzle with combined equilibrium/frozen flow

[igowithit]

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.

 

[igowithit]

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