A wing for use in an aircraft, the wing comprising: a main wing with a supporting main wing structure, a wing end piece with a supporting wing end piece structure, and a lever kinematics for performing a pivoting motion of the wing end piece relative to the main wing between an extended state in which the wing end piece and the main wing form a continuous aerodynamic body and retracted state in which the wing end piece is folded inward with regard to the main wing from the extended state, the lever kinematics comprising: at least a first and a second lever arrangement (H1, H2), which are mounted with a respective first hinged device (162a, 262a; 62a-1, 62a-2) on the main wing structure, and with a respective second hinged device (162b, 262b; 62b-1, 62b-2) on the wing end piece structure, wherein the second hinged device (162b, 262b) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-40) of the wing end piece with regard to each other, and the first hinged device (162a, 262a) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-20) of the main wing with regard to each other, wherein each hinged device (162a, 262a; 62a-1, 62a-2, 162b, 262b; 62b-1, 62b-2) forms a rotational axis, characterized in that the wing end piece structure is expanded in the wingspan direction by means of at least one extension along the main wing structure, at the end of which, in the wingspan direction (SWR-40) of the wing end piece structure opposite the wing tip of the wing, one of the two hinged devices of the lever kinematics is arranged on the wing end piece structure, wherein the extension lengthens the wing end piece structure, thereby generating an intersection between the wing end piece structure and the main wing structure. a main wing with a supporting main wing structure, a wing end piece with a supporting wing end piece structure, and a lever kinematics for performing a pivoting motion of the wing end piece relative to the main wing between an extended state in which the wing end piece and the main wing form a continuous aerodynamic body and retracted state in which the wing end piece is folded inward with regard to the main wing from the extended state, the lever kinematics comprising: at least a first and a second lever arrangement (H1, H2), which are mounted with a respective first hinged device (162a, 262a; 62a-1, 62a-2) on the main wing structure, and with a respective second hinged device (162b, 262b; 62b-1, 62b-2) on the wing end piece structure, wherein the second hinged device (162b, 262b) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-40) of the wing end piece with regard to each other, and the first hinged device (162a, 262a) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-20) of the main wing with regard to each other, wherein each hinged device (162a, 262a; 62a-1, 62a-2, 162b, 262b; 62b-1, 62b-2) forms a rotational axis, characterized in that the wing end piece structure is expanded in the wingspan direction by means of at least one extension along the main wing structure, at the end of which, in the wingspan direction (SWR-40) of the wing end piece structure opposite the wing tip of the wing, one of the two hinged devices of the lever kinematics is arranged on the wing end piece structure, wherein the extension lengthens the wing end piece structure, thereby generating an intersection between the wing end piece structure and the main wing structure. at least a first and a second lever arrangement (H1, H2), which are mounted with a respective first hinged device (162a, 262a; 62a-1, 62a-2) on the main wing structure, and with a respective second hinged device (162b, 262b; 62b-1, 62b-2) on the wing end piece structure, wherein the second hinged device (162b, 262b) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-40) of the wing end piece with regard to each other, and the first hinged device (162a, 262a) of the first lever arrangement and the second hinged device (62b-1, 62b-2) of the second lever arrangement are offset in a wingspan direction (SWR-20) of the main wing with regard to each other, wherein each hinged device (162a, 262a; 62a-1, 62a-2, 162b, 262b; 62b-1, 62b-2) forms a rotational axis, characterized in that the wing end piece structure is expanded in the wingspan direction by means of at least one extension along the main wing structure, at the end of which, in the wingspan direction (SWR-40) of the wing end piece structure opposite the wing tip of the wing, one of the two hinged devices of the lever kinematics is arranged on the wing end piece structure, wherein the extension lengthens the wing end piece structure, thereby generating an intersection between the wing end piece structure and the main wing structure.