Patent ID: 8186619

Claim:
A wing arrangement of an aircraft, comprising a wing and a pylon for suspending an engine below the wing, said wing having a leading edge provided with a high- lift device which is able to move between at least two positions, one being a deployed position in which said high-lift device projects forward of said leading edge in order to increase a lift coefficient of said wing during flight at a high angle of attack, said high-lift device being interrupted in a forward intermediate region of said wing that is situated at said leading edge, the pylon having a forward edge extending substantially forward of the leading edge of the wing between a forward upper portion connected to said wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine, wherein the pylon has, on the forward edge, a protruding element of narrow elongate shape that is oriented substantially in a longitudinal direction of said forward edge, such that during flight at a high angle of attack of the aircraft, the protruding element generates at least one vortex of the aerodynamic flow that is propagated toward the forward intermediate region above the wing; and the protruding element is arranged at the surface of the forward edge of the pylon substantially along an aerodynamic flow separation line which separates regions of the forward edge of the pylon in which stream lines of the aerodynamic flow propagate on opposite lateral flanks of the pylon during flight at a low angle of attack of the aircraft.