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Variable gamma computations for a forward-firing Space Shuttle Main EngineA procedure for solving an axisymmetric SSME nozzle exhausting with an equivalent mass flow of two nozzles is presented for the return-to-launch-site (RTLS) maneuver for an engine-out case. The algorithm incorporates a two-species variable gamma formulation along with diffusion terms associated with a species conservation equation. Coupling of this algorithm is accomplished explicitly to the Navier-Stokes PARC2DR and PARC3DR codes. Axisymmetric results indicate a very complicated flowfield with a bow shock extending to approximately 570 radii in front of the nozzle, and low temperatures on what would be an external tank (ET) aft of the nozzle.
Document ID
19920046982
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Saladino, A. J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Praharaj, S. C.
(REMTECH, Inc. Huntsville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-0840
Accession Number
92A29606
Funding Number(s)
CONTRACT_GRANT: NAS8-38185
Distribution Limits
Public
Copyright
Other

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