Aircraft wing and wing tip device

Patent metadata

Field	Value
Publication number	US-11447239-B2
Application number	US-201916391878-A
Country	US
Kind code	B2
Filing date	Apr 23, 2019
Priority date	Apr 25, 2018
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

An aircraft wing (2) including a main wing (3) and a wing tip device (4) at the tip of the main wing (3), wherein the wing tip device (4) has a variation of leading edge droop with respect to unrolled span-wise position such that flow separation on the wing tip device (4) first occurs in an outboard region (O) of the wing tip device (4). The leading edge droop of the wing tip device (4) may be a maximum in an outboard region (O) of the wing tip device.

First claim

The invention claimed is:

1. An aircraft wing comprising:
a main wing, and
a wing tip device at a tip of the main wing,
wherein the wing tip device includes an upper surface and a lower surface each spanning between a leading edge and a trailing edge of the wing tip device;
wherein the wing tip device has a variation of leading edge droop with respect to unrolled span-wise position such that flow separation on the wing tip device first occurs in an outboard region of the wing tip device,
wherein the leading edge droop, at each unrolled span-wise location of the wing tip device, is characterized by a parameter Droop LE defined as an offset at a leading edge point of the unrolled span-wise location between a local chord line extending through the leading edge point and the trailing edge at the unrolled span-wise location, and a reference line at the unrolled span-wise location extending through the trailing edge and through a reference point mid-way between the upper surface and the lower surface at a reference chord-wise position for the wing tip device, and
wherein a maximum value of the parameter Droop LE for the wing tip device is at least twice a value of the parameter Droop LE at a tip of the wing tip device.

2. The aircraft wing according to claim 1 , wherein the variation of leading edge droop is such that the flow separation on the wing tip device first occurs at, or in a region proximal to, a tip of the wing tip device.

3. The aircraft wing according to claim 1 , wherein the leading edge droop of the wing tip device is a maximum in the outboard region of the wing tip device.

4. The aircraft wing according to claim 3 , wherein the leading edge droop decreases outboard from its a maximum value, towards a tip of the wing tip device.

5. The aircraft wing according to claim 4 , wherein the leading edge droop decreases outboard from the maximum value to the tip of the wing tip device.

6. The aircraft wing according to claim 3 , wherein the variation of leading edge droop is such that the flow separation moves inboard as an angle of attack of the wing tip device is increased.

7. The aircraft wing according to claim 6 , wherein the leading edge droop decreases inboard from the maximum value, towards an inboard end of the wing tip device.

8. The aircraft wing according to claim 1 , wherein the wing tip device comprises a transition region extending from an inboard end where, in an inboard direction, the leading edge droop approaches a value of leading edge droop at the tip of the main wing.

9. The aircraft wing according to claim 8 , wherein the leading edge droop at an outboard end of the transition region is less than an maximum leading edge droop.

10. The aircraft wing according to claim 1 , wherein the wing tip device has increasing dihedral in an outboard direction.

11. The aircraft wing according to claim 1 , wherein the wing tip device is swept back.

12. The aircraft wing according to claim 11 , wherein the leading edge sweep angle of the wing tip device increases in an outboard direction such that the leading edge is curved when viewed in plan form.

13. The aircraft wing according to claim 1 , wherein the wing tip device is a winglet.

14. A wing tip device, for use as the wing tip device in claim 1 , wherein the wing tip device has a variation of the leading edge droop with respect to the unrolled span-wise position such that flow separation on the wing tip device first occurs in the outboard region of the wing tip device.

15. An aircraft comprising an aircraft wing according to claim 1 .

16. The aircraft wing of claim 1 , wherein the outboard region includes a tip of the wing tip device, and the tip is at an outermost span of the wing tip device.

17. The aircraft wing of claim 16 , wherein the wing tip device turns gradually upwards from a root of the wing tip device to the tip.

18. An aircraft wing comprising:
a main wing, and
a wing tip device at a tip of the main wing,
wherein the wing tip device includes an upper surface and a lower surface each spanning between a leading edge and a trailing edge of the wing tip device;
wherein the wing tip device has a variation of leading edge droop with respect to unrolled span-wise position such that the leading edge droop of the wing tip device is a maximum in an outboard region of the wing tip device,
wherein the leading edge droop, at each unrolled span-wise location of the wing tip device, is characterized by a parameter Droop LE defined as an offset at a leading edge point of the unrolled span-wise location between a local chord line extending through the leading edge point and the trailing edge at the unrolled span-wise location, and a reference line at the unrolled span-wise location extending through the trailing edge and through a reference point mid-way between the upper surface and the lower surface at a reference chord-wise position for the wing tip device, and
wherein a maximum value of the parameter Droop LE for the wing tip device is at least twice a value of the parameter Droop LE at a tip of the wing tip device.

19. A wing tip device, for use as the wing device in claim 18 , wherein the wing tip device has a variation of leading edge droop with respect to unrolled span-wise position such that the leading edge droop of the wing tip device is a maximum in an outboard region of the wing tip device.

20. The aircraft wing of claim 18 , wherein the outboard region includes a tip of the wing tip device and the tip is at an outermost span of the wing tip device.

21. The aircraft wing of claim 20 , wherein the wing tip device turns gradually upwards from a root of the wing tip device to the tip.

22. A method of making a wing tip device, for use as part of an aircraft wing, wherein the method comprises:
making the wing tip device with a variation of leading edge droop with respect to unrolled span-wise position such that flow separation on the wing tip device first occurs in an outboard region of the wing tip device,
wherein the wing tip device includes an upper surface and a lower surface each spanning between a leading edge and a trailing edge of the wing tip device;
wherein the leading edge droop, at each unrolled span-wise location of the wing tip device, is characterized by a parameter Droop LE defined as an offset at a leading edge point of the unrolled span-wise location between a local chord line extending through the leading edge point and the trailing edge at the unrolled span-wise location, and a reference line at the unrolled span-wise location extending through the trailing edge and through a reference point mid-way between the upper surface and the lower surface at a reference chord-wise position for the wing tip device, and
wherein a maximum value of the parameter Droop LE for the wing tip device is at least twice a value of the parameter Droop LE at a tip of the wing tip device.

23. The method of claim 22 , wherein the outboard region includes a tip of the wing tip device and the tip is at an outermost span of the wing tip device.

24. The method of claim 23 , wherein the wing tip device turns gradually upwards from a root of the wing tip device to the tip.

Assignees

• Airbus Operations Ltd

Inventors

• Commis Ben
• Lyons Neil John

Classifications

• B64C3/14

  Aerofoil profile · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• B64C23/065 Primary

  at the wing tips · CPC title

• B64C23/069 Primary

  using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title

• Y02T50/10

  Drag reduction · CPC title