Modification of turbulent airfoil section flow using a combined control action
V.I. Kornilov, I.N. Kavun, A.N. Popkov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: крыловой профиль, турбулентный пограничный слой, мелкоперфорированные секции, вдув/отсос, аэродинамическое сопротивление, подъемная сила, аэродинамическое качество, airfoil section, turbulent boundary layer, finely perforated sections, blowing/suction, aerodynamic drag, lift force, lift-to-drag ratio
Abstract
Both numerically and experimentally, the possibility of using a combined method to control the incompressible turbulent boundary layer on a symmetric airfoil section of 12-% relative thickness implemented via the blow-ing/suction of air through a finely perforated section provided on the wing surface part was examined. The study was performed at Reynolds number Rec = 0.7x106 in the range of angles of attack α = -6 - 6º. The mechanism of action of this flow control method on the aerodynamic characteristics of the wing was identified. An ambiguous pattern of the effect due to blowing/suction from the viewpoint of ensuring a maximum lift, a gain in wing lift-to-drag ratio, and a reduction of wing aerodynamic drag was revealed.
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