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A numerical simulation of the inviscid flow through a counterrotating propellerThe results of a numerical simulation of the time-averaged inviscid flow field through the blade rows of a multiblade row turboprop configuration are presented. The governing equations are outlined along with a discussion of the solution procedure and coding strategy. Numerical results obtained from a simulation of the flow field through a modern high-speed turboprop will be shown.
Document ID
19870038121
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Celestina, M. L. (NASA Lewis Research Center Cleveland, OH, United States)
Mulac, R. A. (Sverdrup Technology, Inc. Middleburg Heights, OH, United States)
Adamczyk, J. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 13, 2013
Publication Date
October 1, 1986
Publication Information
Publication: ASME, Transactions, Journal of Turbomachinery
Volume: 108
ISSN: 0889-504X
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 86-GT-138
Accession Number
87A25395
Distribution Limits
Public
Copyright
Other

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