A unified Navier-Stokes flowfield and performance analysis of liquid rocket enginesTo 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.
Document ID
19900053583
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wang, Ten-See (NASA Marshall Space Flight Center Huntsville, AL, United States)
Chen, Yen-Sen (SECA, Inc. Huntsville, AL, United States)