Investigation of the influence of control surfaces and fuselage on the structure of a separated flow around a flying vehicle model with a classical configuration
A.M. Pavlenko, E.A. Melnik, N.S. Alpatskii, B.Yu. Zanin
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: boundary layer, local separation of the flow, laminar-turbulent transition, stall, reverse flow, straight wing, ailerons, fuselage
Abstract
The paper describes the results of an experimental study of the influence of control surfaces and fuselage on the structure of a separated flow around a model of a small-size unmanned flying vehicle with a straight leading edge of the wing. The use of oil-soot visualization and hot-wire anemometry shows that the separation region location depends on the attitude of control surfaces, while the presence of a fuselage leads to reduction of the critical angle of attack.
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