Computational fluid dynamics (CFD) analysis is providing verification of Space Shuttle flight performance details and is being applied to Space Shuttle Main Engine Multiple plume interaction flow field definition. Advancements in real-gas CFD methodology that are described have allowed definition of exhaust plume flow details at Mach 3.5 and 107,000 ft. The specific objective includes the estimate of flow properties at oblique shocks between plumes and plume recirculation into the Space Shuttle Orbiter base so that base heating and base pressure can be modeled accurately. The approach utilizes the Rockwell USA Real Gas 3-D Navier-Stokes (USARG3D) Code for the analysis. The code has multi-zonal capability to detail the geometry of the plumes based region and utilizes finite-rate chemistry to compute the plume expansion angle and relevant flow properties at altitude correctly. Through an improved definition of the base recirculation flow properties, heating, and aerodynamic design environments of the Space Shuttle Vehicle can be further updated.
Computational Fluid Dynamics Analysis of Space Shuttle Main Engine Multiple Plume Flows at High-Altitude Flight Conditions
1992
22 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Fluid Mechanics , Computational fluid dynamics , Exhaust gases , Flow distribution , Plumes , Space shuttle main engine , Flight characteristics , Flight conditions , Navier-stokes equation , Propulsion system performance , Space shuttle orbiters , Applications programs (Computers) , Flow characteristics , High altitude , Real gases , Space transportation system flights
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