Laminar Flow Control on a Swept Wing with Distributed Roughness
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The work cumulated in a series of laminar-turbulent transition flight-test experiments on a swept wing with the goal of validating the spanwise-periodic distributed roughness elements (DRE) technology in a Reynolds number range applicable to SensorCraft technology. Phase I of the program measured freestream turbulence levels that were nominally 0.05% to 0.06% of the freestream speed and thus established the suitability of the flight environment for the laminarization flights. Phase II of the program did the baseline transition measurements on the airfoil i.e. with and without DRE technology. The region of laminar flow was extended from 30% to 60% chord at a chord Reynolds number of Rec = 8 106 and sweep angle, = 30. Copyright 2008 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
name of conference
26th AIAA Applied Aerodynamics Conference
Collection of Technical Papers - AIAA Applied Aerodynamics Conference
author list (cited authors)
Carpenter, A., Saric, W., & Reed, H.
complete list of authors
Carpenter, Andrew||Saric, William||Reed, Helen