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

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Title: Computations of Laminar Flow Control on Swept Wings as a Companion to Flight Test Research
Author: Rhodes, Richard G.
Abstract: 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
URI: http : / /hdl .handle .net /1969 .1 /ETD -TAMU -2008 -12 -96
Date: 2010-01-14

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Computations of Laminar Flow Control on Swept Wings as a Companion to Flight Test Research. Available electronically from http : / /hdl .handle .net /1969 .1 /ETD -TAMU -2008 -12 -96 .

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