Study of distributed suction of the boundary layer influencing the flow past a 3d roughness element on a straight wing model
M.M. Katasonov, V.S. Kaprilenskaya, V.V. Kozlov, A.M. Pavlenko
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: straight wing, flow separation, laminar-turbulent transition, suction for boundary layer, 3D rightness element on a surface
Abstract
A model of straight wing was used for study of the effect of distributed flow suction on the flow structure and on disturbance growth in the boundary layer past a single 3D roughness element installed on the wing surface (at Reynolds number Rec = 240 000). This kind of suction reduces the intensity of natural velocity pulsations by factor of 5. The acoustic-enhanced disturbance intensity drops by 90 times. The effect of distributed suction on the middle flow occurs due to eliminating the flow separation at the trail end of the wing. At the zone downstream the suction site, the boundary layer becomes laminar and uniform (two-dimensional) for the entire span of the wing.
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