Separated flow around a swept wing: the role of fuselage and elevons
A.M. Pavlenko, N.S. Alpatsky, B.Yu. Zanin, E.M. Dubovitsky
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: local flow separation, global separation, reverse flow, boundary layer, laminar-turbulent transition, swept wing, elevons, fuselage
Abstract
Investigation results concerning the influence of fuselage and control surfaces deflection on various types of separation that occur in the flow past a swept-leading-edge wing model at subsonic flow velocities in a wind tunnel are presented. This work continues an experimental series on the study of separated flows and the possibilities of flow control around aircraft wing models at low Reynolds numbers. Using proven methods for visualizing the flow near the wing surface and hot-wire measurements, experimental data were obtained that provide a comprehensive understanding of the separation structures that arise on the leeward side of the wing model at various angles of attack and control surface deflections. The issue of flow separation control is also examined. It is shown that global flow separation can be eliminated using the method of local influence at specific points.
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