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Airplane wing with a system creating a laminar boundary layer flow

A boundary layer and airfoil technology, applied in the field of aircraft wings, can solve the problems of weight loss, cleaning and icing, expensive porous surface, etc., achieve good tolerance and avoid ice growth

Inactive Publication Date: 2016-08-24
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, porous surfaces are expensive, have drawbacks regarding cleaning and freezing, and there is a weight loss due to the plumbing required

Method used

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  • Airplane wing with a system creating a laminar boundary layer flow
  • Airplane wing with a system creating a laminar boundary layer flow
  • Airplane wing with a system creating a laminar boundary layer flow

Examples

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Embodiment Construction

[0038] figure 1 , 2 , 5, 6 and 7 show embodiments of an aircraft wing 10 according to the invention. Aircraft wing 10 is a swept aircraft wing of an aircraft having a leading edge 12 that includes a line of attachment 14 . The attachment line 14 is the region where air impinging on it flows into the boundary layer along the leading edge 12 along the span.

[0039]Above the attachment line 14 , air 15 flows over the upper surface 16 of the aircraft wing 10 . Below the attachment line 14 , air 17 flows over the lower surface 18 of the aircraft wing 10 . Along the leading edge 12, the aircraft wing 10 has an arrangement 20 of slats configured to improve high-lift performance.

[0040] The slat arrangement 20 has at least one first slat 22 and a second slat 24 between which there is a slat-to-slat joint 26 .

[0041] like Figure 5 As indicated, the slat arrangement 20 may have more than two slats, such as three, four, five or more slats.

[0042] When observing the attachm...

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PUM

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Abstract

In order to form a laminar adhesion line flow, the present invention proposes an aircraft wing, which includes: a leading edge, the leading edge includes an adhesion line, and the adhesion line is an area in which the air hitting the area moves along the leading edge. Flow into the boundary layer along the spanwise direction; a first slat and a second slat, wherein the leading edge and the attachment line are at least partially formed at the first and second slats, in a downstream direction of the attachment line flow, the second The slat is adjacent the first slat such that the leading edge includes a slat-to-slat joint, wherein the slat cavity forms the slat-to-slat joint below a skin region of at least one of the first and second slats ; and a duct having a duct inlet at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing, the duct being at least partially formed by the slat cavity, wherein the duct inlet is The duct inlet extends around the leading edge and throughout the location of the slat-to-slat attachment line.

Description

technical field [0001] The invention relates to an aircraft wing. The invention relates in particular to an aircraft wing with a system or device for creating a laminar boundary layer flow over said wing. Background technique [0002] The wings of conventional aircraft have movable devices called slats that are positioned along the wing's leading edge to improve high-lift performance. The slats are retracted during the cruise phase of flight. At the leading edge of a swept wing, which is typically used in transonic aircraft, there is spanwise flow from the root to the tip, above which the air flows over the upper surface, and below the tip the air flow over the lower surface. This flow is called attached line flow. The presence of slats or other types of movable high-lift devices (eg flap devices) introduces surface discontinuities (steps and slots) on the spanwise leading edge. The presence of these discontinuities means that the spanwise attachment line flow will be t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C21/02B64C21/06B64C9/24
CPCB64C2230/22B64C9/24B64C21/06Y02T50/30Y02T50/10B64C9/26B64C21/02
Inventor 斯蒂芬·罗尔斯顿
Owner AIRBUS OPERATIONS GMBH