A wing, particularly an airfoil of an aircraft, having a changeable profile, which extends in the wing depth direction (5) running essentially in the flow direction and transversely thereto in the wing span direction and has a first planking (55a) and a second planking (55b), and having a flexible area (11), through which the profile of the wing (1) is adjustable, is described. The flexible area (11) may comprise one or more than one vortex elements (154'') extending in a longitudinal direction, which are connected to one another in an articulated way on their longitudinal sides in a predefined dimension via joint areas (169'') and between which the first planking (55a) and the second planking (55b) are provided, the vortex elements (154'') having a transmission area (164''), which runs transversely to their longitudinal direction and is connected to the first planking (55a), and a drive or adjustment area (163''), which is at a distance in the vertical direction and is coupled to an adjustment mechanism (505'') for moving the vortex elements (154'') around the joint areas (169''), the adjustment mechanism (505'') containing one or more lever elements (507''), which are coupled between the drive or adjustment area (163'') of the lever elements (154'') and the second planking (55b) and are rotatable or pivotable by one or more drive elements (509'') so as to mutually displace drive or adjustment area (163'') and second planking (55b) to change the wing profile in response to a corresponding externally supplied control signal.