Journal
PHILOSOPHICAL TRANSACTIONS OF THE ROYAL SOCIETY A-MATHEMATICAL PHYSICAL AND ENGINEERING SCIENCES
Volume 369, Issue 1940, Pages 1352-1364Publisher
ROYAL SOC
DOI: 10.1098/rsta.2010.0368
Keywords
laminar flow control; three-dimensional boundary layers; transition; discrete roughness
Categories
Funding
- Air Force Research Laboratories, WPAFB
- Air Force Office of Scientific Research
- Northrop-Grumman Corporation
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A brief review of laminar flow control techniques is given and a strategy for achieving laminarization for transonic transport aircraft is discussed. A review of some flight-test results on swept-wing transition is presented. It is also shown that polished leading edges can create large regions of laminar flow because the flight environment is relatively turbulence free and the surface finish reduces the initial amplitude of the stationary crossflow vortex.
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