Wing for an aircraft

A wing for an aircraft, the wing comprising:

• a wing body having a wingtip, a leading-edge, and a trailing edge,
• wherein the wingtip comprises an outboard-most portion of the wing,
• wherein the leading-edge is disposed along a forward portion of the wing body and is configured such that when the aircraft is flown sub-sonically at a first predetermined angle of attack, a vortex will form at the leading-edge and create a low pressure region at a first location on an upper surface of the wing, and when the aircraft is flown sub-sonically at a second predetermined angle of attack greater than the first predetermined angle of attack, the vortex will be repositioned causing the low pressure region to move to a second location on the upper surface of the wing, the second location being aft and inboard of the first location, and
• wherein the trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip and at a position that corresponds with the second location and wherein the trailing edge inboard of the aft-most region extends continuously upstream and includes at least one break.

A wing for an aircraft, the wing comprising:

• a wing body having a wingtip, a leading-edge, and a trailing edge,
• wherein the wingtip comprises an outboard-most portion of the wing body;
• wherein the leading-edge is disposed along a forward portion of the wing body and is configured such that when the aircraft is flown sub-sonically at a first predetermined angle of attack, a vortex will form at the leading-edge, the vortex having a vortex axis extending outboard in a first direction that is substantially aligned with the leading-edge when the aircraft is flown at the first predetermined angle of attack, and the vortex axis extending outboard in a second direction that is oblique with respect to the leading-edge and aft thereof when the aircraft is flown at a second predetermined angle of attack, the second predetermined angle of attack being greater than the first predetermined angle of attack;
• and
• wherein the trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip and at a position that corresponds with the vortex axis when the aircraft is flown at the second predetermined angle of attack and wherein the trailing edge inboard of the aft-most region extends continuously upstream and includes at least one break.