Wing tip shape for a wing, in particular of aircraft

Patent metadata

Field	Value
Publication number	US-9550563-B2
Application number	US-201414252173-A
Country	US
Kind code	B2
Filing date	Apr 14, 2014
Priority date	Nov 21, 2006
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction.

First claim

The invention claimed is:

1. A wing tip device for a wing of an aircraft, wherein the wing tip device comprises:
a substantially planar winglet;
a transition region connected to the substantially planar winglet;
wherein the wing tip device is configured to be mounted on an end of the wing,
wherein the end of the wing comprises a profile that is delimited by a first skin and a second skin,
wherein the transition region extends from a first connection on the wing to a second connection on the substantially planar winglet,
wherein geometric parameters of the substantially planar winglet are configured to reduce induced drag, and
wherein the transition region has a non-constant curvature distribution of the local dihedral to reduce interference effects.

2. The wing tip device of claim 1 , wherein in the transition region the radius of curvature of the local dihedral decreases over at least substantially 50% of a spanwise dimension of the transition region in the outboard direction up to a maximum.

3. The wing tip device of claim 1 , wherein in the transition region the radius of curvature of the local dihedral decreases over at least substantially 75% of a spanwise dimension of the transition region in the outboard direction up to a maximum.

4. The wing tip device of claim 1 , wherein in the transition region the radius of curvature of the local dihedral decreases over at least substantially 90% of a spanwise dimension of the transition region in the outboard direction up to a maximum.

5. The wing tip device of claim 2 , wherein in the transition region the radius of curvature of the local dihedral begins to decrease at the first connection of the transition region.

6. The wing tip device of claim 1 , wherein the wing tip shape extends at maximum over a region of 5 to 20% of a semispan of the wing.

7. The wing tip device of claim 1 , wherein the wing tip extends at maximum over a region of 10% of a semispan of the wing.

8. The wing tip device of claim 1 , wherein the substantially planar winglet extends over at least 50% of the total height of the wing above the wing.

9. The wing tip device of claim 1 , wherein the substantially planar winglet has a cant angle of up to 45 degrees.

10. The wing tip device of claim 1 , wherein the substantially planar winglet has a cant angle of up to 60 degrees.

11. The wing tip device of claim 1 , wherein the substantially planar winglet has a cant angle of up to 80 degrees.

12. The wing tip device of claim 1 , wherein the tangent line of the local dihedral is continuous at the first connection of the transition region.

13. The wing tip device of claim 1 , wherein the tangent line of the local dihedral is continuous at the second connection of the transition region.

14. The wing tip device of claim 1 , wherein, at the first connection, a leading edge of the transition region transits at a continuous tangent line to a leading edge of the wing.

15. The wing tip device of claim 1 , wherein at least one of the sweep on the leading edge of the transition region and a sweep on a leading edge of the substantially planar winglet continuously increases in the outboard direction up to a point of largest sweep.

16. The wing tip device of claim 15 , wherein the leading edge of the transition region transits at a continuous tangent line from the point of largest sweep to a leading edge of the substantially planar winglet.

17. The wing tip device of claim 15 , wherein the point of largest sweep on the leading edge of the transition region is at more than 75% of the unrolled length of the transition region, calculated from the first connection to the second connection.

18. The wing tip device of claim 1 , wherein a tangent line of the leading edge is continous over the entire transition region.

Assignees

• Airbus Operations Gmbh
• Deutsches Zentrum Für Luft- Und Raumfahrt E V (Dlr)

Inventors

• Theurich Frank
• Himisch Jan

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64C23/065 Primary

  at the wing tips · CPC title

• Y02T50/164

  Cross-Sectional Technologies · mapped topic

• B64C23/069 Primary

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