Wing tip device
View Patent ↗An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.
1. An aircraft comprising a wing, the wing comprising a tip and a wing tip device mounted in the region of the tip, the wing tip device being generally downwardly extending and having a region inclined at a cant of more than 180 degrees, the region being arranged to generate lift during flight, wherein the wing tip device comprises a plurality of discrete elements, at least one element being located in the region inclined at a cant of more than 180 degrees.
2. An aircraft according to claim 1 , wherein the wing has a positive dihedral.
3. An aircraft according to claim 1 , wherein the region inclined at a cant of more than 180 degrees is inclined at a cant of less than 270 degrees.
4. An aircraft according to claim 1 , the wing tip device comprising a proximal end and a distal end, wherein the wing tip device extends in a spanwise direction from the proximal end, a distance between 3% and 15% of the aircraft span.
5. An aircraft according to claim 1 , the wing tip device comprising a proximal end and a distal end, wherein the wing tip device extends in a vertical direction from the proximal end, a distance between 3% and 15% of the aircraft span.
6. An aircraft according to claim 1 , wherein the wing tip device leading edge is swept.
7. An aircraft according to claim 1 , wherein at least one of the wing or the wing tip device is arranged to deform during use, to provide the aircraft with a larger span in comparison to when the aircraft is stationary.
8. An aircraft, comprising a fuselage and a wing attached to the fuselage,
the wing comprising a tip and a wing tip device,
the wing tip device being generally downwardly extending and having a region inclined at a cant of more than 180 degrees, said region being arranged to generate lift during flight,
the wing tip device comprising a proximal end and a distal end, the proximal end being attached to the tip of the wing,
wherein said region is not located in the vicinity of the proximal end, and wherein the wing tip device comprises a plurality of discrete elements which are serially connected to each other from the proximal end to the distal end, and at least one of which defines said region.
9. An aircraft according to claim 8 , wherein the wing has a positive dihedral.
10. An aircraft according to claim 8 , wherein said region is inclined at a cant of less than 270 degrees.
11. An aircraft according to claim 8 , wherein
the wing tip device contains a notional line starting at the proximal end, extending to the distal end and passing, at all points, through 50% local chord of the wing tip device, and
said region is not located between the proximal end and 30% of the notional line.
12. An aircraft according to claim 8 , wherein
the wing tip device contains a notional line starting at the proximal end, extending to the distal end and passing, at all points, through 50% local chord of the wing tip device, and
said region is, at least partially, located between 50% of the notional line and the distal end.
13. An aircraft according to claim 12 , wherein said region is located in the vicinity of the distal end.
14. An aircraft according to claim 8 , wherein a distance in a spanwise direction from the proximal end to the distal end of the wing tip device is between 3% and 15% of the aircraft span.
15. An aircraft according to claim 8 , wherein a distance in a vertical direction from the proximal end to the distal end of the wing tip device is between 3% and 15% of the aircraft span.
16. An aircraft according to claim 8 , wherein the wing tip device has a leading edge that is swept.
17. An aircraft according to claim 8 , wherein at least one of the wing or the wing tip device is arranged to deform during use, to provide the aircraft with a larger span in comparison to when the aircraft is stationary.
18. A wing including a wing tip device, the wing and wing tip device being arranged in accordance with the wing of the aircraft according to claim 8 .
19. A wing tip device arranged in accordance with the wing tip device of the aircraft according to claim 8 .
20. An aircraft, comprising a fuselage and a wing attached to the fuselage,
the wing comprising a tip and a wing tip device,
the wing tip device being generally downwardly extending and having a region inclined at a cant of more than 180 degrees, said region being arranged to generate lift during flight,
the wing tip device comprising a proximal end and a distal end, the proximal end being attached to the tip of the wing,
wherein said region is closer to the distal end than to the proximal end, and wherein the wing tip device comprises a plurality of discrete elements, at least one element being located in the region inclined at a cant of more than 180 degrees.