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Three-dimensional calculation of supersonic reacting flows using an LU schemeA new three-dimensional numerical program incorporated with comprehensive real gas property models was developed to simulate supersonic reacting flows. The code employs an implicit finite volume, Lower-Upper (LU) time-marching method to solve the complete Navier-Stokes and species equations in a fully-coupled and very efficient manner. A chemistry model with nine species and eighteen reaction steps are adopted in the program to represent the chemical reaction of H2 and air. To demonstrate the capability of the program, flow fields of underexpanded hydrogen jets transversely injected into supersonic air stream inside the combustors of scramjets are calculated. Results clearly depict the flow characteristics, including the shock structure, separated flow regions around the injector, and the distribution of the combustion products.
Document ID
19910001558
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Yu, Sheng-Tao (Sverdrup Technology, Inc. Cleveland, OH, United States)
Tsai, Y-L Peter (Sverdrup Technology, Inc. Cleveland, OH, United States)
Shuen, Jian-Shun (Sverdrup Technology, Inc. Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1989
Publication Information
Publication: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12
Subject Category
Aerodynamics
Accession Number
91N10871
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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