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A three-dimensional incompressible flow simulation method and its application to the Space Shuttle main engine. II Turbulent flowAn implicit finite difference code cast in general curvilinear coordinates is further developed for three-dimensional incompressible turbulent flows. The code is based on the method of pseudocompressibility and utilizes the Beam and Warming implicit approximate factorization algorithm to achieve computational efficiency. A multiple-zone method is further extended to include composite-grids to overcome the excessive computer memory required for solving turbulent flows in complex three-dimensional geometries. A simple turbulence model is proposed for internal flows. The code is being used for the Space Shuttle Main Engine (SSME) internal flow analyses.
Document ID
19850060949
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chang, J. L. C.
(Rockwell International Corp. Canoga Park, CA, United States)
Rosen, R.
(Rockwell International Corp. Canoga Park, CA, United States)
Dao, S. C.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Kwak, D.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 85-1670
Accession Number
85A43100
Funding Number(s)
CONTRACT_GRANT: NAS8-27980
Distribution Limits
Public
Copyright
Other

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