Body tab yaw deflector
US-2017341730-A1 · Nov 30, 2017 · US
Wing and aircraft
US10988233B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10988233-B2 |
| Application number | US-201716307672-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 21, 2017 |
| Priority date | Jun 13, 2016 |
| Publication date | Apr 27, 2021 |
| Grant date | Apr 27, 2021 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
[Solving Means] A wing 1 is typically used as a main wing of an aircraft 100. The wing 1 is a swept-back wing having a swept-back angle A. The wing 1 is configured such that a surface pressure (pressure distribution (Cp)) on an upper surface of a vicinity of a leading edge 11 in a fluid increases from a wing root 17 to a wing tip 15. A cross-flow component of an external streamline of a surface of the wing 1 is reduced in the vicinity of the leading edge 11, and boundary layer transition is not easily induced in the vicinity of the leading edge 11. With this, friction drag caused by cross-flow instability can be reduced.
First claim
Opening claim text (preview).
The invention claimed is: 1. A wing having a swept-back angle, which is configured such that a surface pressure on an upper surface of a vicinity of a leading edge of the wing in a fluid increases from a wing root to a wing tip, wherein the vicinity of the leading edge of the wing is within a range of 0% to 5% from the leading edge of the wing in a wing chord direction, and wherein the wing is configured such that a rising gradient of the surface pressure on the upper surface of the vicinity of the leading edge of the wing in the fluid is systematically gentler from the wing root to the wing tip. 2. The wing according to claim 1 , which is configured such that a non-dimensionalized radius of curvature of the leading edge increases from the wing root to the wing tip. 3. The wing according to claim 2 , which is configured such that a dimensionalized radius of curvature of the leading edge decreases from the wing root to the wing tip. 4. The wing according to claim 1 , wherein the surface pressure on the upper surface of the vicinity of the leading edge in the fluid is expressed by a function of Expression 1 below: [ Expression 1 ] Cp ( ξ , η ) = ∑ i = 0 n A i ( η ) f i ( ξ , η ) ξ ≡ x / c , η ≡ y / s f 0 ( ξ , η ) ≡ 1 , f i ( ξ , η ) ≡ exp [ B i ( η ) ξ p i ] - 1 , i = 1 , … , n - 1 f n
Assignees
Inventors
Classifications
Frontal aspect · CPC title
for supercritical or transonic flow · CPC title
Supersonic type aircraft · CPC title
- B64C3/10Primary
Shape of wings · CPC title
Drag reduction · CPC title
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- What does patent US10988233B2 cover?
- [Solving Means] A wing 1 is typically used as a main wing of an aircraft 100. The wing 1 is a swept-back wing having a swept-back angle A. The wing 1 is configured such that a surface pressure (pressure distribution (Cp)) on an upper surface of a vicinity of a leading edge 11 in a fluid increases from a wing root 17 to a wing tip 15. A cross-flow component of an external streamline of a surface…
- Who is the assignee on this patent?
- Japan Aerospace Exploration
- What technology area does this patent fall under?
- Primary CPC classification B64C3/10. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Apr 27 2021 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).