Rocket Nozzle with combined equilibrium/frozen flow

Click For Summary
SUMMARY

The discussion focuses on using the NASA CEA code to analyze the specific impulse (Isp) and thrust data for the Space Shuttle Main Engine (SSME) under varying flow conditions. The user successfully solves the problem for both frozen and equilibrium flow conditions but seeks guidance on how to implement a combined approach, where equilibrium flow is applied from the combustion chamber to the nozzle throat and frozen flow from the throat to the nozzle exit. The NASA CEA code allows for individual flow condition analysis but does not directly support this hybrid approach, necessitating further exploration of the code's capabilities.

PREREQUISITES
  • Familiarity with NASA CEA code version used for rocket propulsion analysis
  • Understanding of frozen flow and equilibrium flow concepts in rocket nozzle design
  • Knowledge of specific impulse (Isp) and thrust calculations for rocket engines
  • Basic principles of thermodynamics as applied to combustion processes
NEXT STEPS
  • Research the NASA CEA code documentation for advanced flow condition configurations
  • Explore hybrid flow modeling techniques in rocket propulsion
  • Learn about the implications of flow conditions on nozzle performance and efficiency
  • Investigate case studies involving combined flow conditions in rocket nozzle design
USEFUL FOR

Aerospace engineers, propulsion specialists, and students studying rocket propulsion who are interested in advanced flow modeling techniques and the application of NASA CEA code for performance analysis.

igowithit
Messages
6
Reaction score
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.
 
Physics news on Phys.org
bump
 

Similar threads

Liquid rocket engine excercise
  • · Replies 1 ·
Replies
1
Views
1K
Rocket thrust equation in under-expanded nozzle
  • · Replies 2 ·
Replies
2
Views
5K
Graduate Optimal Size of Rocket Engine Nozzle for Vacuum Performance
  • · Replies 26 ·
Replies
26
Views
3K
Understanding High Thrust of Vacuum Rocket Engines
  • · Replies 2 ·
Replies
2
Views
4K
Mass flow rate through De Laval Nozzle
  • · Replies 1 ·
Replies
1
Views
5K
I on my rocket engine thrust equation
  • · Replies 2 ·
Replies
2
Views
3K
Conv-Div nozzle and Fanno flow (Gas Dynamics)
  • · Replies 1 ·
Replies
1
Views
4K
Is there a limit on rocket engine exhaust velocity?
  • · Replies 16 ·
Replies
16
Views
8K
Graduate Validity of rocket pressure thrust term
  • · Replies 11 ·
Replies
11
Views
5K
The vacuum optimized Raptor: No attempt at an expander-bleed cycle
  • · Replies 11 ·
Replies
11
Views
4K