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The Split Coefficient Matrix method for hyperbolic systems of gasdynamic equationsThe Split Coefficient Matrix (SCM) finite difference method for solving hyperbolic systems of equations is presented. This new method is based on the mathematical theory of characteristics. The development of the method from characteristic theory is presented. Boundary point calculation procedures consistent with the SCM method used at interior points are explained. The split coefficient matrices that define the method for steady supersonic and unsteady inviscid flows are given for several examples. The SCM method is used to compute several flow fields to demonstrate its accuracy and versatility. The similarities and differences between the SCM method and the lambda-scheme are discussed.
Document ID
19800034116
Document Type
Conference Paper
Authors
Chakravarthy, S. R. (Rockwell International Science Center Thousand Oaks, Calif., United States)
Anderson, D. A. (Iowa State University of Science and Technology, Ames, Iowa, United States)
Salas, M. D. (NASA Langley Research Center High Speed Aerodynamics Div., Hampton, Va., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 80-0268
Meeting Information
Aerospace Sciences Meeting(Pasadena, CA)
Funding Number(s)
CONTRACT_GRANT: NSG-1535
Distribution Limits
Public
Copyright
Other