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A device for adapting aerodynamic characteristics of a wing element, includes a winglet, movably attachable to a wing element. The winglet or parts of the winglet may be rotatable in relation to the wing element such that an associated rotary axis with a main direction of extension of the wing eleme

A device for adapting aerodynamic characteristics of a wing element, includes a winglet, movably attachable to a wing element. The winglet or parts of the winglet may be rotatable in relation to the wing element such that an associated rotary axis with a main direction of extension of the wing element encompasses an angle that differs from an angle of 90°. In addition, a method is disclosed.

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1. An adaption device for adapting aerodynamic characteristics of a wing element, comprising: a winglet movably attachable to the wing element, wherein the winglet is attachable on an attachment axis to the wing element, such that the winglet is rotatable around the attachment axis as a rotary axis

1. An adaption device for adapting aerodynamic characteristics of a wing element, comprising: a winglet movably attachable to the wing element, wherein the winglet is attachable on an attachment axis to the wing element, such that the winglet is rotatable around the attachment axis as a rotary axis having a rotary axis direction, and an angle between the rotary axis direction and a direction of a main axis of extension of the wing element differs from 90°, wherein the direction of the main axis of extension is perpendicular to an axial direction along the axis of an aircraft fuselage to which the wing element is attached. 2. The device of claim 1, wherein the winglet is rotatable in relation to the wing element on three rotary axes, the rotary axis of claim 1 being one of the three rotary axes. 3. The device of claim 1, further comprising the wing element. 4. The device of claim 1, further comprising an aerodynamic fairing element between the wing element and the winglet or a portion of the winglet. 5. The device of claim 1, further comprising at least one suspension element attaching the winglet to the wing element. 6. The device of claim 5, wherein the at least one suspension element is controllably movable. 7. The device of claim 5, wherein the at least one suspension element is movable by means of a driven spindle. 8. The device of claim 1, further, comprising a drive device for moving the winglet. 9. The device of claim 8, wherein the drive device is selected from the group consisting of electric, hydraulic, piezoelectric drives and active materials. 10. The device of claim 9, wherein the drive device is selected as a piezoceramic active material. 11. The device of claim 1, wherein the winglet is divided into an upper part and a lower part, wherein of the upper part of the winglet, the lower part of the winglet or both thereof are movable. 12. The device of claim 11, wherein the upper part, the lower part or both thereof are divided into a plurality of sub-parts, and at least one of the plurality of sub-parts is designed so as to be movable. 13. The device of claim 1, wherein the winglet comprises an upper part, a lower part and an outer part, wherein one or more of the upper part, the lower part or the outer part of the winglet is designed so as to be movable. 14. The device of claim 1, wherein in addition to the winglet, a part of the wing element or an entire wing element, including the winglet, is adapted for being rotatable. 15. A locomotion device, comprising an adaption device for adapting aerodynamic characteristics of a wing element of claim 1. 16. The locomotion device of claim 15, wherein the locomotion device is an aircraft. 17. A method for adapting aerodynamic characteristics of a wing element, comprising the step of rotating on two rotary axes a winglet that is attached to the wing element in relation to the wing element such that an angle between one of the two rotary axes, having a first rotary axis direction and a direction of a main axis of extension of the wing element differs from 90°, wherein the direction of the main axis of extension is perpendicular to an axial direction along the axis of an aircraft fuselage to which the wing element is attached. 18. The method of claim 17, wherein the step of rotating the winglet includes providing an onboard computer unit, for controlling the winglet on the basis of measured aircraft data. 19. The method of claim 17, wherein the step of providing onboard computer unit includes providing the onboard computer unit comprising a regulating unit adapted for regulating a rotation of the winglet. 20. The method of claim 19, wherein the step of providing includes providing the regulating unit as an adaptive regulating unit, wherein the adaptive regulating unit is capable of adapting to a plurality of flight parameters and aircraft parameters. 21. The method of claim 17, wherein the method includes controlling wing torsion using the winglet. 22. The method of claim 17, wherein the method includes controlling wing bending.