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Wing tip devices for aircraft wings

A technology of aircraft and wings, applied in the field of wing tip equipment, can solve the problems of aircraft payload capacity reduction, wing effective angle of attack reduction, fuel efficiency reduction, etc.

Active Publication Date: 2019-06-28
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

A slight rearward tilt of the wing's lift can also be described as a reduction in the effective angle of attack of the wing, and can result in a decrease in the payload capacity of the aircraft, and / or in the endurance of the aircraft, and / or in fuel efficiency

Method used

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  • Wing tip devices for aircraft wings
  • Wing tip devices for aircraft wings
  • Wing tip devices for aircraft wings

Examples

Experimental program
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Embodiment Construction

[0027] Referring now to the drawings, which are shown for purposes of illustrating various embodiments of the present disclosure, figure 1 Shown is a front view of an aircraft 100 having a pair of wings 200 and incorporating an example of a wing tip device 300 coupled to each wing 200 . As described in more detail below, various embodiments of the wing tip apparatus 300 disclosed herein include an upper winglet 302 and a lower member 398 . Advantageously, the combination of upper winglet 302 and lower element 398 provides wing trailing edge 206 ( Figure 5 ) increases in effective length. In this way, wing tip device 300 allows for a reduction in the induced drag produced by wing 200 .

[0028] exist figure 1 In this example, an aircraft 100 may include a fuselage 104 having a longitudinal axis 106 that may extend lengthwise along the fuselage 104 . As noted above, the aircraft 100 may include a pair of wings 200 that may be attached to the fuselage 104 . Each wing 200 ma...

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PUM

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Abstract

The present invention relates to a wing tip device for an aircraft wing, which may comprise an upper winglet and a lower element. An upper winglet may extend upwardly from the aircraft wing. The lower element may extend downwardly from the upper winglet and may form a closed loop under the wing. The closed loop may have a hollow interior.

Description

technical field [0001] The present invention relates generally to aerodynamics, and more particularly to wing tip devices such as wings for aircraft. Background technique [0002] The induced drag of an aircraft wing may be described as aerodynamic drag, which results from the change in direction of the air above the wing as the wing moves through the air. The change in direction of the air may include a spanwise flow of air along the underside of the wing, which is generally towards the outboard direction of the wing tip. When the spanwise airflow reaches the wing tip, the air flows up over the wing tip and joins the chordwise airflow moving over the top of the wing. The combination of spanwise and chordwise airflow results in the formation of vortices at the wing tips. [0003] This wing tip vortex is fed by other vortices that flow out as it travels down the trailing edge of the wing. The downward motion of the wing tip vortex and trailing edge vortex causes the lift o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/36
CPCB64F5/50B64C23/069B64C23/065Y02T50/10
Inventor A·A·扎曼
Owner THE BOEING CO