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Combustion chamber analysis codeA three-dimensional, time dependent, Favre averaged, finite volume Navier-Stokes code has been developed to model compressible and incompressible flows (with and without chemical reactions) in liquid rocket engines. The code has a non-staggered formulation with generalized body-fitted-coordinates (BFC) capability. Higher order differencing methodologies such as MUSCL and Osher-Chakravarthy schemes are available. Turbulent flows can be modeled using any of the five turbulent models present in the code. A two-phase, two-liquid, Lagrangian spray model has been incorporated into the code. Chemical equilibrium and finite rate reaction models are available to model chemically reacting flows. The discrete ordinate method is used to model effects of thermal radiation. The code has been validated extensively against benchmark experimental data and has been applied to model flows in several propulsion system components of the SSME and the STME.
Document ID
19940006462
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Przekwas, A. J. (Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Lai, Y. G. (Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Krishnan, A. (Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Avva, R. K. (Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Giridharan, M. G. (Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
CFDRC-4105/6
NAS 1.26:192585
NASA-CR-192585
Accession Number
94N10934
Funding Number(s)
CONTRACT_GRANT: NAS8-37824
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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