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Application of laminar flow control to high-bypass-ratio turbofan engine nacellesRecently, the concept of the application of hybrid laminar flow to modern commercial transport aircraft was successfully flight tested on a Boeing 757 aircraft. In this limited demonstration, in which only part of the upper surface of the swept wing was designed for the attainment of laminar flow, significant local drag reduction was measured. This paper addresses the potential application of this technology to laminarize the external surface of large, modern turbofan engine nacelles which may comprise as much as 5-10 percent of the total wetted area of future commercial transports. A hybrid-laminar-flow-control (HLFC) pressure distribution is specified and the corresponding nacelle geometry is computed utilizing a predictor/corrector design method. Linear stability calculations are conducted to provide predictions of the extent of the laminar boundary layer. Performance studies are presented to determine potential benefits in terms of reduced fuel consumption.
Document ID
19920057341
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wie, Y. S.
(High Technology Corp. Hampton, VA, United States)
Collier, F. S., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Wagner, R. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
September 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
SAE PAPER 912114
Accession Number
92A39965
Funding Number(s)
CONTRACT_GRANT: NAS1-18240
Distribution Limits
Public
Copyright
Other

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