Wing, aircraft, and method for delaying wing stall of an aircraft

Patent metadata

Field	Value
Publication number	US-11214351-B2
Application number	US-201815997343-A
Country	US
Kind code	B2
Filing date	Jun 4, 2018
Priority date	Jun 4, 2018
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A wing includes: an inner end configured to be coupled to a fuselage of an aircraft; an inboard section extending from the inner end; a fixed leading edge of the inboard section having a drooped contour positioned along at least a portion thereof; and an outboard section extending from the inboard section.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage having a forward end and an aft end;
a wing coupled to the fuselage, the wing having a leading edge and a trailing edge, the wing having a wing root and a wing tip, wherein the wing ends in a free end at the wing tip, wherein a distance between the leading edge and the trailing edge at the wing root is greater than a distance between the leading edge and the trailing edge at the wing tip; and
a jet engine coupled to an underside of the wing, wherein a front of the engine is forward of the leading edge of the wing;
one or more moveable leading edge devices along a first portion of the leading edge outboard of the jet engine,
wherein, inboard of the jet engine, the leading edge comprises a fixed drooped contour along at least a portion thereof,
wherein the fixed drooped contour is inboard of an inboard edge of the jet engine,
wherein the wing is a rearward-swept wing.

2. The aircraft of claim 1 wherein the trailing edge comprises one or more moveable trailing edge devices.

3. The aircraft of claim 1 wherein, in a cross-section of the fixed drooped contour, a lower wing skin extending from the leading edge has a positive change in slope proximate to the leading edge and a negative change in slope further from the leading edge.

4. The aircraft of claim 3 wherein, in the cross-section of the fixed drooped contour, the lower wing skin has another positive change in slope even further from the leading edge than the negative change in slope.

5. The aircraft of claim 4 wherein, in the cross-section of the fixed drooped contour, the slope of the lower wing skin is negative proximate to the leading edge, positive further from the leading edge, and negative even further from the leading edge.

6. The aircraft of claim 4 wherein, in the cross-section of the fixed drooped contour, the slope of the lower wing skin is negative proximate to the leading edge and further from the leading edge.

7. A method for delaying wing stall of the aircraft of claim 1 , the method comprising:
flying the aircraft at a cruising speed, wherein the cruising speed is greater than the speed of sound.

8. The method of claim 7 , further comprising moving a moveable leading edge device and decelerating the aircraft to a landing speed.

9. The method of claim 8 further comprising moving a moveable leading edge device outboard of an engine and accelerating the aircraft to a takeoff speed.

10. The aircraft of claim 1 wherein the wing is coupled to the fuselage by way of a side-of-body joint.

11. The aircraft of claim 1 wherein most of a length of the leading edge between the jet engine and the fuselage has the fixed drooped contour.

12. The aircraft of claim 1 wherein the wing comprises an upper wing skin, a lower wing skin, and a spar between the upper wing skin and lower wing skin.

13. The aircraft of claim 1 further comprising a vertical stabilizer fixed to the fuselage and a horizontal stabilizer fixed to the fuselage.

14. The aircraft of claim 1 wherein a rear of the jet engine is aft of the leading edge of the wing.

15. The aircraft of claim 11 wherein a rear of the jet engine is aft of the leading edge of the wing.

16. The aircraft of claim 13 wherein a rear of the jet engine is aft of the leading edge of the wing.

17. The aircraft of claim 1 wherein the trailing edge has a rearward sweep.

18. The aircraft of claim 11 wherein the trailing edge has a rearward sweep.

19. The aircraft of claim 13 wherein the trailing edge has a rearward sweep.

20. The aircraft of claim 14 wherein the trailing edge has a rearward sweep.

Assignees

• Boeing Co

Inventors

• Hoffenberg Robert
• Malachowski Adam P
• Smith Bonnie R
• Adamson Eric E

Classifications

• B64C3/14 Primary

  Aerofoil profile · CPC title

• B64C9/24

  by single flap · CPC title

• B64C2003/146

  comprising leading edges of particular shape · CPC title

• B64D27/18

  within, or attached to, wings · CPC title

• B64C2003/149

  for supercritical or transonic flow · CPC title