Aerodynamic tip feature

1. An aircraft defining a longitudinal direction, a vertical direction, and a transverse direction, the aircraft comprising:

a fuselage; and

a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction,

wherein the wing comprises a wing tip assembly at the outer end of the wing,

wherein the wing tip assembly defines an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis,

wherein the wing tip assembly comprises at least three stationary guide vanes spaced along the circumferential direction from one another,

wherein the wing tip assembly has an axis segment having a set length that extends along the axis, and

wherein base portions of each of the at least three stationary guide vanes extend at least partially around the axis segment.

2. The aircraft of claim 1 , wherein the wing tip assembly comprises at least 4 and less than 20 stationary guide vanes spaced along the circumferential direction from one another.

3. The aircraft of claim 1 , wherein each of the stationary guide vanes of the wing tip assembly are spaced substantially equally from one another along the circumferential direction.

4. The aircraft of claim 1 ,

wherein each of the stationary guide vanes of the wing tip assembly define a length, and

wherein the lengths of at least two of the stationary guide vanes of the wing tip assembly are substantially equal to one another.

5. The aircraft of claim 4 , wherein the lengths of each of the stationary guide vanes of the wing tip assembly are substantially equal to one another.

6. The aircraft of claim 1 , wherein the stationary guide vanes of the wing tip assembly define a variable spacing between one another along the circumferential direction.

7. The aircraft of claim 6 , wherein a spacing between each adjacent pair of stationary guide vanes is less than an angle defined by the equation 360°/(n+1)+180°/(n+1), and greater than an angle defined by the equation 360°/(n+1)−180°/(n+1), where “n” is equal to the number of stationary guide vanes.

8. The aircraft of claim 1 ,

wherein the stationary guide vanes of the wing tip assembly includes a first set of stationary guide vanes and a second set of stationary guide vanes,

wherein the first set of stationary guide vanes each define a first length,

wherein the second set of stationary guide vanes each define a second length, and

wherein the first length is greater than the second length.

9. The aircraft of claim 8 , wherein the first set of stationary guide vanes is alternatingly spaced with the second set of stationary guide vanes.

10. The aircraft of claim 1 ,

wherein the wing further comprises a wing body, wherein the wing tip assembly is coupled to, or formed integrally with, the wing body, and wherein the at least 3 stationary guide vanes of the wing tip assembly are further spaced along the circumferential direction from the wing body.

11. The aircraft of claim 1 , wherein the stationary guide vanes of the wing tip assembly are each fixed in position.

12. The aircraft of claim 1 ,

wherein the wing further comprises a wing body defining an aft edge, and

wherein each of the stationary guide vanes of the wing tip assembly defines an aft edge, and

wherein the aft edges of the stationary guide vanes are at least partially aligned with the aft edge of the wing body or positioned at least partially aft of the aft edge of the wing body.

13. The aircraft of claim 1 ,

wherein the wing is a first wing, and

wherein the aircraft further comprises:

a second wing extending from the fuselage generally along the transverse direction on an opposite side of the fuselage from the first wing,

wherein the second wing also defines an outer end along the transverse direction and includes a wing tip assembly at the outer end,

wherein the wing tip assembly of the second wing defines an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis,

the wing tip assembly of the second wing also comprising at least three stationary guide vanes spaced from one another along the circumferential direction of the wing tip assembly of the second wing.

14. The aircraft of claim 1 , wherein a first stationary guide vane of the at least three stationary guide vanes of the wing tip assembly defines a leading edge having a substantially concave shape.

15. The aircraft of claim 1 ,

wherein a first stationary guide vane of the at least three stationary guide vanes of the wing tip assembly defines a leading edge and a trailing edge,

wherein the wing defines a trailing edge at the outer end, and

wherein the leading edge of the first stationary guide vane is at least partially forward of the trailing edge of the wing, and

wherein the trailing edge of the first stationary guide vane is at least partially aft of the trailing edge of the wing.