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A pressure correction method for the calculation of compressible chemical reacting flowsA recently developed noniterative method for the solution of the transient fluid flow equations at all speed is extended to handle chemical reacting flows. The species conservation equations are loosely coupled into the predictor/multicorrector sequence of the solution procedure. A split-operator method separates the chemical kinetics terms from the fluid-dynamical terms, as well as an implicit differencing method enhance the numerical stability. The method was applied for turbulent diffusion flame calculations and for the analyses of high pressure, axisymmetric turbulent hypersonic nozzle flows. The diffusion flame results were compared with a similar pressure method for fast chemistry integration scheme without operator-splitting. Simulations of the nozzle flow indicated that the nonideal intermolecular effects must be included in the analysis and design of high pressure hypersonic nozzle.
Document ID
19920064408
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chen, Z. J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Chen, C. P.
(Alabama, University Huntsville, United States)
Chen, Y. S.
(Engineering Sciences, Inc. Huntsville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Inorganic And Physical Chemistry
Report/Patent Number
AIAA PAPER 92-3032
Accession Number
92A47032
Funding Number(s)
CONTRACT_GRANT: NAG8-128
Distribution Limits
Public
Copyright
Other

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