A flat plate rectangular wing subjected to grid - generated turbulence

A flat plate rectangular wing subjected to grid - generated turbulence

Cruz, E, Watkins, S, Loxton, B and Watmuff, J 2008, 'A flat plate rectangular wing subjected to grid - generated turbulence', in Kevin C Massey (ed.) 26th AIAA Applied Aerodynamics Conference, Washington D.C., United States, 18-21 August, 2008.

Document type:	Conference Paper
Collection:	Conference Papers

Title	A flat plate rectangular wing subjected to grid - generated turbulence
Author(s)	Cruz, E Watkins, S Loxton, B Watmuff, J
Year	2008
Conference name	26th AIAA Applied Aerodynamics Conference
Conference location	Washington D.C., United States
Conference dates	18-21 August, 2008
Proceedings title	26th AIAA Applied Aerodynamics Conference
Editor(s)	Kevin C Massey
Publisher	AIAA
Place of publication	Washington D.C., United States
Abstract	Micro air vehicles (MAVs) are low speed, small, remotely piloted aircraft designed for low altitude reconnaissance and sensory missions. The low speed flight through the lower levels of the atmospheric boundary layer results in relatively high turbulence levels and low Reynolds numbers. In recent studies of low Reynolds number airfoils, the effects of turbulence are rarely considered nor replicated, since traditionally aeronautical testing is almost always conducted in smooth flow. In this paper turbulence intensities comparable to those experienced by MAVs flying at low speed and altitude are replicated via grids in a wind tunnel. A thin, pressure-tapped, flat-plate aerofoil was used to investigate the effects of Reynolds number and turbulence on coefficients of pressure, lift, drag and pitching moment. The lift at high angles of attack was found to increase with raised turbulence intensity, although a drag penalty was incurred.
Subjects	Aerodynamics (excl. Hypersonic Aerodynamics) Aerospace Engineering not elsewhere classified Mechanical Engineering not elsewhere classified
Keyword(s)	aerodynamics flat plate airfoil turbulence
Copyright notice	Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc.
ISSN	1048-5953

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