A wing for an aircraft, the wing comprising: a main wing section extending between a root portion and a distal portion, the main wing section having a forward spar and an aft spar extending through an internal cavity of the main wing section along a span thereof, the forward and aft spars (14A, 14B) being spaced apart in a chordwise direction at the distal portion of the main wing section and delimiting a dry segment of the internal cavity; a winglet rotatably coupled to the main wing section by a cant hinge defining a cant axis about which the winglet rotates relative to the main wing section, the winglet being movable between an extended position in which the winglet is aligned with the main wing section, and a folded position in which the winglet is rotated about the cant axis; and a linkage assembly disposed in the dry segment of the internal cavity of the main wing section, the linkage assembly pivotably mounted to one of the forward and aft spars (14A, 14B) and coupled to the cant hinge, the linkage assembly being displaceable to apply a force to the cant hinge to move the winglet between the extended position and the folded position during flight of the aircraft; wherein the linkage assembly is a first linkage assembly pivotably mounted to the forward spar, the wing further comprising a second linkage assembly disposed in the dry segment, and pivotably mounted to the aft spar and coupled to the cant hinge, the second linkage assembly being displaceable to apply the force to the cant hinge to move the winglet between the extended position and the folded position during flight of the aircraft; and wherein the first linkage assembly comprises: a first linear actuator having a first actuator housing pivotably mounted to the forward spar, and a first piston rod displaceable relative to the first actuator housing; a first crank pivotably mounted to the forward spar, and pivotably coupled to the first piston rod to be displaced thereby; and a first toggle having a first end pivotably coupled to the first crank and a second end pivotably coupled to the cant hinge; and the second linkage assembly comprises: a second linear actuator having a second actuator housing mounted to the aft spar, and a second piston rod displaceable relative to the second actuator housing; a second crank pivotably mounted to the aft spar, and pivotably coupled to the second piston rod to be displaced thereby; and a second toggle having a first end pivotably coupled to the second crank and a second end pivotably coupled to the cant hinge. a main wing section extending between a root portion and a distal portion, the main wing section having a forward spar and an aft spar extending through an internal cavity of the main wing section along a span thereof, the forward and aft spars (14A, 14B) being spaced apart in a chordwise direction at the distal portion of the main wing section and delimiting a dry segment of the internal cavity; a winglet rotatably coupled to the main wing section by a cant hinge defining a cant axis about which the winglet rotates relative to the main wing section, the winglet being movable between an extended position in which the winglet is aligned with the main wing section, and a folded position in which the winglet is rotated about the cant axis; and a linkage assembly disposed in the dry segment of the internal cavity of the main wing section, the linkage assembly pivotably mounted to one of the forward and aft spars (14A, 14B) and coupled to the cant hinge, the linkage assembly being displaceable to apply a force to the cant hinge to move the winglet between the extended position and the folded position during flight of the aircraft; wherein the linkage assembly is a first linkage assembly pivotably mounted to the forward spar, the wing further comprising a second linkage assembly disposed in the dry segment, and pivotably mounted to the aft spar and coupled to the cant hinge, the second linkage assembly being displaceable to apply the force to the cant hinge to move the winglet between the extended position and the folded position during flight of the aircraft; and wherein the first linkage assembly comprises: a first linear actuator having a first actuator housing pivotably mounted to the forward spar, and a first piston rod displaceable relative to the first actuator housing; a first crank pivotably mounted to the forward spar, and pivotably coupled to the first piston rod to be displaced thereby; and a first toggle having a first end pivotably coupled to the first crank and a second end pivotably coupled to the cant hinge; and the second linkage assembly comprises: a second linear actuator having a second actuator housing mounted to the aft spar, and a second piston rod displaceable relative to the second actuator housing; a second crank pivotably mounted to the aft spar, and pivotably coupled to the second piston rod to be displaced thereby; and a second toggle having a first end pivotably coupled to the second crank and a second end pivotably coupled to the cant hinge. a second linear actuator having a second actuator housing mounted to the aft spar, and a second piston rod displaceable relative to the second actuator housing; a second crank pivotably mounted to the aft spar, and pivotably coupled to the second piston rod to be displaced thereby; and a second toggle having a first end pivotably coupled to the second crank and a second end pivotably coupled to the cant hinge.