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A numerical simulation of the inviscid flow through a counter-rotating 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
19860006725
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Celestina, M. L. (Sverdrup Technology, Inc. Cleveland, Ohio, United States)
Mulac, R. A. (Sverdrup Technology, Inc. Cleveland, Ohio, United States)
Adamczyk, J. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
E-2855
NAS 1.15:87200
NASA-TM-87200
Report Number: E-2855
Report Number: NAS 1.15:87200
Report Number: NASA-TM-87200
Meeting Information
Meeting: International Gas Turbine Conference
Location: Dusseldorf
Country: Germany
Start Date: June 8, 1986
End Date: June 12, 1986
Sponsors: ASME
Accession Number
86N16195
Funding Number(s)
PROJECT: RTOP 505-90-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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