| 摘要 |
The invention relates to a wing, especially the carrier wing of an aeroplane , said wing having an adaptable profile that extends in the wing chord directi on (5) running essentially in the direction of flow, and in the wingspan direction (10), perpendicularly to the wing chord direction. The inventive wing comprises a first coating (55a) and a second coating (55b) opposite sai d first coating, in addition to a front edge region (11) and a rear edge regio n (12) in terms of the wing chord direction (5), and a wing tip region (14) at the end of the wing (1) in terms of the wingspan direction (10). According t o the invention, a flexible region (15) arranged close to the end of the wing enables the profile of the wing tip region (14) to be adjusted in a directio n containing both a component in the wing chord direction (5) and a component in the wingspan direction (10).
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