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Development of the KIVA-2 CFD code for rocket propulsion applicationsThe KIVA-2 code, originally developed to solve computational fluid dynamics problems in internal combustion engines, has been developed to solve rocket propulsion type flows. The objective of the work was to develop a code such that both liquid and solid particle motion could be simulated for arbitrary geometry and high speed as well as low speed reacting flows. Modification to the original code include: incorporating independently specific supersonic and subsonic inflows and outflows; symmetric as well as periodic boundary conditions; and the capability to use generalized single or multi-specie thermodynamic data and transport coefficients allowing the user to specify arbitrary wall temperature/heat flux distributions. This code has been shown to successfully solve rocket propulsion flows as well as flows with entrained particles for several different rocket nozzles.
Document ID
19920023028
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shannon, Robert V., Jr.
(Aerotherm Corp. Huntsville, AL, United States)
Murray, Alvin L.
(Aerotherm Corp. Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Publication Information
Publication: NASA. Goddard Space Flight Center, Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 2
Subject Category
Spacecraft Propulsion And Power
Accession Number
92N32272
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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