A unified Navier-Stokes flowfield and performance analysis of liquid rocket engines
Abstract
To improve the current composite solutions in the design and analysis of liquid propulsive engines, a computational fluid dynamics model capable of calculating the nonreacting and reacting flows from the combustion chamber, through the nozzle to the external plume, was developed. The Space Shuttle Main Engine (SSME) fired at sea level, along with the flowfields of several other nozzles were investigated. The bell-shaped SSME nozzle was run at 100 percent power level at various flow conditions, the computed flow results and performance compared well with those of other standard codes and engine hot fire test data.
- Publication:
-
AIAA, SAE, ASME, and ASEE, 26th Joint Propulsion Conference
- Pub Date:
- July 1990
- Bibcode:
- 1990jpof.confR....W
- Keywords:
-
- Computational Fluid Dynamics;
- Finite Difference Theory;
- Liquid Propellant Rocket Engines;
- Navier-Stokes Equation;
- Propulsion System Performance;
- Combustion Chemistry;
- Computational Grids;
- Rocket Nozzles;
- Space Shuttle Main Engine;
- Supersonic Flow;
- Fluid Mechanics and Heat Transfer