Vortex structure of separated flows on model wings at low freestream velocities

• Published in: Fluid dynamics Vol. 43; no. 6; pp. 938 - 944
• Main Authors: Zanin, B. Yu, Zverkov, I. D., Kozlov, V. V., Pavlenko, A. M.
• Format: Journal Article
• Language: English
• Published: Dordrecht SP MAIK Nauka/Interperiodica 01-12-2008
• Subjects: Classical and Continuum Physics; Classical Mechanics; Computational fluid dynamics; Engineering Fluid Dynamics; Fluid flow; Fluid- and Aerodynamics; Laminar boundary layer; Physics; Physics and Astronomy; Separated flow; Separation; Stall; Vortices; Wing flow; experimental study; flow separation; model wings; large-scale vortices
• ISSN: 0015-4628; 1573-8507
• DOI: 10.1134/S0015462808060148

Flow past model wings is experimentally investigated in a subsonic wind tunnel at large angles of attack at which the laminar boundary layer separates near the leading edge of the wing (flow stall). The object of the study was the flow structure within the separation zone. The carbon-oil visualization of surface streamlines used in the experiments showed that in the separation zone there exist one or more pairs of large-scale vortices rotating in the wing plane. Certain general properties of the vortex structures in the separation zone are found to exist, whereas the flow patterns may differ depending on the model aspect ratio, the yaw angle, and other factors.