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The computation of supersonic combustor flows using multi-computersAn explicit CFD computer code with parallel processing is developed for the purpose of simulating internal high-speed reacting flows. The code solves the 3D Navier-Stokes equations for compressible flows. Preliminary results indicate that parallel processing should solve the resource and speed shortages presently encountered with sequential computers for problems of interest.
Document ID
19930036176
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Underwood, Mark (NASA Langley Research Center Hampton, VA, United States)
Riggins, David (NASA Langley Research Center Hampton, VA, United States)
Mcmillin, Bruce (NASA Langley Research Center Hampton, VA, United States)
Lu, Eric J.-L. (NASA Langley Research Center Hampton, VA, United States)
Reeves, Larry (Missouri-Rolla Univ. Rolla, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1993
Subject Category
Computer Programming And Software
Report/Patent Number
AIAA PAPER 93-0060
Report Number: AIAA PAPER 93-0060
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A20173
Funding Number(s)
CONTRACT_GRANT: NSF MSS-92-16479
CONTRACT_GRANT: F49620-92-J-0546
Distribution Limits
Public
Copyright
Other

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