Winglet and method of designing a winglet

1. An aircraft comprising:

a wing, and

a winglet at an end of the wing, the winglet comprising: a root, a tip at an upper region of the winglet, a transition region extending away from the root; and a wing-like region extending from a distal end of the transition region to the tip,

wherein, when the aircraft wing is under a worst-case static loading, the tip of the winglet is located at a maximum spanwise extent of the winglet;

wherein, when the aircraft wing is under a no-load condition, the wing-like region is canted inboard with respect to a vertical plane such that the tip of the winglet is located inboard of the maximum spanwise extent of the winglet, and

wherein the winglet while in the no-load condition has a shape corresponding to a jig shape of the winglet.

2. The aircraft according to claim 1 , wherein the wing-like region comprises a planar portion extending to the winglet tip.

3. The aircraft according to claim 2 , wherein when the aircraft wing is under the worst-case static loading, the planar portion extends vertically downward from the winglet tip such that the planar portion lies along the maximum spanwise extent of the winglet, and when the aircraft wing is in the no-load condition the planar portion is canted inboard with respect to the vertical plane.

4. The aircraft according to claim 2 , wherein an entirety of the wing-like region is planar.

5. The aircraft according to claim 1 , wherein when the aircraft is in flight under 1-g flight conditions, the wing-like region is canted further inboard, relative to when the aircraft wing is under the no-load condition, such that the tip of the winglet is located yet further inboard of the maximum span of the winglet.

6. A method of designing a winglet for an aircraft wing, the method comprising the steps of:

(i) determining a maximum allowable wing span for the aircraft wing when it is under worst-case static loading;

(ii) designing the winglet such that, when the aircraft wing is under worst-case static loading, a tip at an upper region of the winglet is located at a maximum winglet span of the winglet and the wing-like region is aligned with a vertical plane, wherein a maximum wing span of the aircraft wing when the winglet is at the maximum winglet span is no greater than the maximum allowable span of the aircraft wing, and

(iii) designing a required jig shape of the winglet to achieve the winglet design of step (ii) by canting a wing-like region of the jig shape of the winglet inboard with respect to the vertical plane to locate the tip of the winglet inboard of the maximum span of the winglet, wherein the wing-like region extends from a tip of the winglet to a transition region of the winglet between the tip and a root of the winglet,

wherein the jig shape of the winglet corresponds to a non-load condition of the winglet and the jig shape of the winglet positions a portion of the winglet beyond the maximum winglet span of the winglet.

7. The method of manufacturing a winglet, comprising:

designing a winglet using the method according to claim 6 ; and subsequently manufacturing the winglet to the design of the winglet.

8. An aircraft comprising a wing and a winglet at an end of the wing, and the winglet includes a wing-like region extending from a tip at an upper region of the winglet to a curved transition region of the winglet, and

wherein when the aircraft wing is under a worst-case static loading, the wing-like region of the winglet extends vertically and upward, and when the aircraft wing is under a no-load condition, the wing-like region of the winglet is canted inboard with respect to a vertical plane such that a tip of the winglet is located inboard of a maximum spanwise extent of the winglet, and

wherein the winglet while in the no-load condition has a shape corresponding to a jig shape of the winglet.