AIRCRAFT WINGLET FLOW LIMITATION CREST Russian patent published in 2021 - IPC B64C3/58 

FIELD: aviation.

SUBSTANCE: aircraft wing consists of front edge of wing, rear edge of wing and wing surface formed by upper surface of wing and lower surface of wing, wherein wing extends from wing root to end of wing, having end chord; winglet, passing from wing end and containing front edge of winglet, located behind wing leading edge, rear edge of winglets, an inner surface of the winglet, an outer surface of the winglet, a winglet root containing a chord of the winglet root, and an end of the winglet; flow limit flange located on the wing surface and spaced from the winglet in the fuselage direction, wherein the flow limit flange overlaps the winglet. At that, the flow limitation flange is configured to generate swirls between the flow restriction flange and the winglet when air flow moves from wing bottom surface to wing top surface around wing tip and wing front edge. At that, the vortexes redirect the air flow to limit the low pressure peaks on the leading edge of the winglet, and with possibility of deceleration and / or prevention of air flow separation on inner surface of winglet at large angles of lateral sliding, which increases lateral stability and aligns aircraft at high sliding angles.

EFFECT: group of inventions also relates to a method of preventing separation of air flow from an inner surface of a winglet and an aircraft wing.

19 cl, 24 dwg