Airbus Operations Gmbh

Ching-Yu Hui

Neil John Lyons

Alan Mann

Christopher Bauer

Chris Foster

An aircraft wing assembly including a main wing portion, a high-lift device with a flow surface including an upper skin portion and a lower skin portion, wherein the flow surface of the high-lift device comprises a first flow surface portion, a second flow surface portion and a third flow surface portion, wherein the first flow surface portion is micro-perforated for an air inflow, wherein the first flow surface portion extends on the upper skin from the leading edge in chordwise direction for 2% or less of the local chord and extends on the lower skin from the leading edge in chordwise direction for 2% or less of the local chord, and wherein the second flow surface portion is not micro-perforated and extends over the rest of the upper skin portion, and wherein the third flow surface portion is not micro-perforated and extends over the rest of the lower skin portion.

Aircraft wing assembly

An aerodynamic structure for use on an upper surface of an aircraft wing is disclosed. The wing includes a slat operable between a stowed configuration in which the slat is stowed in a slat recess of the wing, and a deployed configuration in which the slat extends out of the slat recess. When the slat is in the deployed configuration, an end face of the slat recess is exposed, the end face intersecting with the upper surface of the wing at a recess edge. The aerodynamic structure, adjacent to the recess edge, has a volume shaped to encourage air flowing over the recess edge onto the upper surface during flight, to remain attached.

Aerodynamic structure for aircraft wing

An aerodynamic body for use on an aircraft including at least a first perforated surface portion () and an ice-protection system (). The first perforated surface portion () has perforations. The ice-protection system () includes an actuatable element () and the actuatable element () is movable or deformable between a first position and a second position. In the first position, the actuatable element () is thermally coupled to the first perforated surface portion () and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element () is distanced from the first perforated surface portion () and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

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Bristol, United Kingdom

Ching-Yu Hui