GB2471269A - Chevron wing - Google Patents

Chevron wing Download PDF

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Publication number
GB2471269A
GB2471269A GB0910588A GB0910588A GB2471269A GB 2471269 A GB2471269 A GB 2471269A GB 0910588 A GB0910588 A GB 0910588A GB 0910588 A GB0910588 A GB 0910588A GB 2471269 A GB2471269 A GB 2471269A
Authority
GB
United Kingdom
Prior art keywords
trailing edge
vortices
wing
chevrons
jagged
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB0910588A
Other versions
GB0910588D0 (en
Inventor
Ian Morton Hannay
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to GB0910588A priority Critical patent/GB2471269A/en
Publication of GB0910588D0 publication Critical patent/GB0910588D0/en
Publication of GB2471269A publication Critical patent/GB2471269A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/147—Aerofoil profile comprising trailing edges of particular shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A wing is fitted with a series of chevrons along the trailing edge to reduce the span wise flow and reduce induced drag.

Description

Patent Specification
AEROFOIL TRAILING EDGE MODIFICATION TO REDUCE DRAG.
This is a modification to the trailing edge of an aerofoil or aircraft wing to reduce drag.
It also applies to any air or hydrofoil system, including propellers or rotors.
Induced drag is caused by the spanwise flow around the wingtip.
This modification reduces the spanwise flow and therefore reduces the flow around the tip, reducing the induced drag. The trailing edge vortices are in effect fixed rather than flowing spanwise in the case of a conventional smooth trailing edge.
The wing trailing edge is modified by having a series of chevrons (pointed extensions) mounted stream wise in plan form. (Fig 1) The size and number of the chevrons depends on the application but for optimum efficiency the size should increase towards the wingtip.
The optimum size of chevron is dependant upon the lift of the foil and will be quieter with rounded tips, reducing the intensity of the core of the vortices To be most effective the chevrons should be consecutive or nearly so. Being spaced further apart decreases the effect but is still beneficial.
This gives the appearance of a saw tooth trailing edge, but the chevrons may be of any shape or size. The chevrons may be cut out of the trailing edge or added to it, or a combination of both. The actual shape will depend upon the application.

Claims (3)

  1. CLAIMS1. The difference between conventional wing trailing edges, which is basically a smooth line (straight or curved) and this new style which is jagged.
  2. 2. The jagged points create fixed vortices that reduce span wise flow.
  3. 3. On a conventional wing with smooth trailing edge these trailing edge vortices are allowed to migrate towards the tip, increasing the tip vortex and induced drag.
GB0910588A 2009-06-19 2009-06-19 Chevron wing Withdrawn GB2471269A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0910588A GB2471269A (en) 2009-06-19 2009-06-19 Chevron wing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0910588A GB2471269A (en) 2009-06-19 2009-06-19 Chevron wing

Publications (2)

Publication Number Publication Date
GB0910588D0 GB0910588D0 (en) 2009-07-29
GB2471269A true GB2471269A (en) 2010-12-29

Family

ID=40941080

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0910588A Withdrawn GB2471269A (en) 2009-06-19 2009-06-19 Chevron wing

Country Status (1)

Country Link
GB (1) GB2471269A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020147912A1 (en) * 2019-01-20 2020-07-23 Alameldin Ahmad Mahmoud Bio inspired foil-trailing-edge attachment to increase lift

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1541108A (en) * 1975-06-20 1979-02-21 Deutsche Forsch Luft Raumfahrt Body for location in a fluid flow
US4830315A (en) * 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
US5492289A (en) * 1992-04-28 1996-02-20 British Technology Group Usa Inc. Lifting body with reduced-strength trailing vortices
US5871174A (en) * 1994-01-28 1999-02-16 Hannay; Ian Morton Foils
US7114685B1 (en) * 2004-06-01 2006-10-03 Deutsches Zentrum Fur Luft-Und Wing for an aircraft or spacecraft

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1541108A (en) * 1975-06-20 1979-02-21 Deutsche Forsch Luft Raumfahrt Body for location in a fluid flow
US4830315A (en) * 1986-04-30 1989-05-16 United Technologies Corporation Airfoil-shaped body
US5492289A (en) * 1992-04-28 1996-02-20 British Technology Group Usa Inc. Lifting body with reduced-strength trailing vortices
US5871174A (en) * 1994-01-28 1999-02-16 Hannay; Ian Morton Foils
US7114685B1 (en) * 2004-06-01 2006-10-03 Deutsches Zentrum Fur Luft-Und Wing for an aircraft or spacecraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020147912A1 (en) * 2019-01-20 2020-07-23 Alameldin Ahmad Mahmoud Bio inspired foil-trailing-edge attachment to increase lift

Also Published As

Publication number Publication date
GB0910588D0 (en) 2009-07-29

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)