Patent ID: 8096500

Claim:
A lifting or stabilising component for an aircraft comprising: a tip located at a distal end of said lifting or stabilising component in a spanwise direction; a rotary control element rotating relative to said lifting or stabilising component about an axis of rotation; at least one slot formed between said tip and said rotary control element; and sealing means arranged in said at least one slot for assuring aerodynamic continuity between said lifting or stabilising component and said rotary control element when said rotary control element is at rest; characterised in that the edges of said tip and said rotary control element around said at least one slot are configured such that the distance therebetween is constant for different angles of deflection of the rotary control element; wherein said edges comprise a first section that extends perpendicular to said axis of rotation in the direction of the trailing edge of said lifting or stabilizing component, a second section extending from the first section in a direction opposite the flight direction, and a softened transition area therebetween, the length of said first section being between 5 and 15% of the length of said second section.