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Evaluation of 3 numerical methods for propulsion integration studies on transonic transport configurationsAn effort has been undertaken at the NASA Langley Research Center to assess the capabilities of available computational methods for use in propulsion integration design studies of transonic transport aircraft, particularly of pylon/nacelle combinations which exhibit essentially no interference drag. The three computer codes selected represent state-of-the-art computational methods for analyzing complex configurations at subsonic and transonic flight conditions. These are: EULER, a finitie volume solution of the Euler equation; VSAERO, a panel solution of the Laplace equation; and PPW, a finite difference solution of the small disturbance transonic equations. In general, all three codes have certain capabilities that allow them to be of some value in predicting the flows about transport configurations, but all have limitations. Until more accurate methods are available, careful application and interpretation of the results of these codes are needed.
Document ID
19860017737
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Yaros, S. F. (NASA Langley Research Center Hampton, VA, United States)
Carlson, J. R. (NASA Langley Research Center Hampton, VA, United States)
Chandrasekaran, B. (Vigyan Research Associates, Inc. Hampton, Va., United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-87727
NAS 1.15:87727
AIAA PAPER 86-1814
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: San Diego, CA
Country: United States
Start Date: June 9, 1986
End Date: June 11, 1986
Accession Number
86N27209
Funding Number(s)
PROJECT: RTOP 505-62-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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