Granted Patent B2

US 12,214,865 · App. 18/393,888 · Granted Feb 4, 2025

Inventor: Norman Wood (Bristol, GB)

Assignee: AIRBUS OPERATIONS LIMITED

B64C23/072B64C3/14B64C2003/146

Abstract

Claims (26)

1. A wing tip device, or a wing having a wing tip device, for a fixed wing aircraft, comprising:

a first leading edge region having a first sweep angle,

a second leading edge region outboard of the first leading edge region in a spanwise direction and having a second sweep angle smaller than the first sweep angle,

wherein the first leading edge region is blended into the second leading edge region by a concave junction,

a third leading edge region outboard of the second leading edge region in the spanwise direction and adjacent a tip end of the wing tip device, and having a third sweep angle greater than the first sweep angle,

wherein the second leading edge region is adapted to generate a first vortex,

wherein the third leading edge region is adapted to generate a second vortex which builds towards the tip end of the wing tip device,

wherein a trailing edge of the wing tip device includes a convex portion, and

wherein a tip end connects the convex portion of the trailing edge with the third leading edge of the wing tip device via a concave portion.

2. The wing tip device or a wing according to claim 1 , wherein the first, second and third leading edge regions are located along a single line when the wing tip device is viewed in the aircraft longitudinal direction.

3. The wing tip device or a wing according to claim 1 , wherein the first leading edge region and the second leading edge region are opposing.

4. The wing tip device or a wing according to claim 1 , wherein the first leading edge region is substantially straight.

5. The wing tip device or a wing according to claim 1 , wherein the first sweep angle is at least 20 degrees.

6. The wing tip device or a wing according to claim 1 , wherein the second and third sweep angles are each at least 35 degrees.

7. The wing tip device or a wing according to claim 1 , wherein the second leading edge region is forward swept.

8. The wing tip device or a wing according to claim 1 , wherein the third leading edge region is aft swept.

9. The wing tip device or a wing according to claim 1 , wherein a chord length of the wing tip device in the second leading edge region increases in the outboard spanwise direction.

10. The wing tip device or a wing according to claim 1 , wherein a chord length of the wing tip device in the third leading edge region decreases in the outboard spanwise direction.

11. The wing tip device or a wing according to claim 1 , wherein the second leading edge region is inboard of the tip end of the wing tip device in the spanwise direction.

12. The wing tip device or a wing according to claim 1 , wherein the second leading edge region is blended into the first leading edge region.

13. The wing tip device or a wing according to claim 1 , wherein the second leading edge region extends up to the third leading edge region.

14. The wing tip device or a wing according to claim 13 , wherein the second leading edge region and the third leading edge region meet to form an acute leading edge cusp.

15. The wing tip device or a wing according to claim 13 , wherein the second leading edge region and the third leading edge region meet to form a smooth-continuous leading edge crest.

16. The wing tip device or a wing according to claim 1 , wherein the second leading edge region and the third leading edge region are separated by a notched leading edge region.

17. The wing tip device or a wing according to claim 1 , wherein a lower aerodynamic surface of the wing tip device and/or wing includes a concave portion adjacent the leading edge.

18. The wing tip device or a wing according to claim 17 , wherein the concave portion of the lower aerodynamic surface is provided in an aerofoil section that includes the second leading edge region or the third leading edge region.

Priority Claims (1)

Continuity (2)

References Cited (101)