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
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-2008-12-96 |
| Date | 14 January 2010 |
| Creators | Rhodes, Richard G. |
| Contributors | Reed, Helen L. |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis |
| Format | application/pdf |
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