Rocket Nozzle with combined equilibrium/frozen flow

AI Thread Summary
The discussion revolves around using NASA's CEA code to analyze the specific impulse (Isp) and thrust data for the Space Shuttle Main Engine (SSME) under different flow conditions. The user seeks guidance on how to implement a combined equilibrium flow from the combustion chamber to the nozzle throat and frozen flow from the throat to the nozzle exit, as this scenario was not covered in lectures. They note that the CEA code allows for individual frozen and equilibrium flow analyses but lacks a straightforward method for the combined approach. The user is looking for assistance on how to properly set up this specific case in the CEA code. Clarification on this combined flow scenario is essential for completing their homework.
igowithit
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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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Thread 'Variable mass system : water sprayed into a moving container'

Thread 'Variable mass system : water sprayed into a moving container'

Starting with the mass considerations #m(t)# is mass of water #M_{c}# mass of container and #M(t)# mass of total system $$M(t) = M_{C} + m(t)$$ $$\Rightarrow \frac{dM(t)}{dt} = \frac{dm(t)}{dt}$$ $$P_i = Mv + u \, dm$$ $$P_f = (M + dm)(v + dv)$$ $$\Delta P = M \, dv + (v - u) \, dm$$ $$F = \frac{dP}{dt} = M \frac{dv}{dt} + (v - u) \frac{dm}{dt}$$ $$F = u \frac{dm}{dt} = \rho A u^2$$ from conservation of momentum , the cannon recoils with the same force which it applies. $$\quad \frac{dm}{dt}...
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