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Computations of Laminar Flow Control on Swept Wings as a Companion to Flight Test Research

The high cost of energy has resulted in a renewed interest in the study of
reducing skin-friction drag in aeronautical applications. Laminar Flow Control
(LFC) refers to any technique which alters the basic-state flow-field to delay
transition from laminar to turbulent flow. Achieving fully laminar flow over a
civilian transport wing will significantly reduce drag and fuel costs while increasing
range and performance.
Boundary-layer suction has proven to be an effective means of achieving
laminar flow over an aircraft wing as demonstrated with the Northrop X-21 program;
however, even with the savings in fuel, the high manufacturing and maintenance
costs have discouraged the use of this technology. Recent work using threedimensional
(3-D) spanwise-periodic distributed roughness elements (DREs) has
shown great promise as a means of controlling the crossflow instability responsible
for transition over a swept wing without the need for a complex suction system.
The Texas A

Identiferoai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-2008-12-96
Date14 January 2010
CreatorsRhodes, Richard G.
ContributorsReed, Helen L.
Source SetsTexas A and M University
Languageen_US
Detected LanguageEnglish
TypeBook, Thesis, Electronic Thesis
Formatapplication/pdf

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