GB2472766A - Wing - Google Patents

Wing Download PDF

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Publication number
GB2472766A
GB2472766A GB0912603A GB0912603A GB2472766A GB 2472766 A GB2472766 A GB 2472766A GB 0912603 A GB0912603 A GB 0912603A GB 0912603 A GB0912603 A GB 0912603A GB 2472766 A GB2472766 A GB 2472766A
Authority
GB
United Kingdom
Prior art keywords
wing
bending moment
drag
span
reduced
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Withdrawn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
GB0912603A
Other versions
GB0912603D0 (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 GB0912603A priority Critical patent/GB2472766A/en
Publication of GB0912603D0 publication Critical patent/GB0912603D0/en
Publication of GB2472766A publication Critical patent/GB2472766A/en
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • 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)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

By reducing the loading on the outer portion of a wing, the bending moment can be reduced with little increase in drag, allowing for a lighter wing structure compared to a conventional wing.

Description

KUDOWA WING.
Wing Lift Distribution.
On conventional wings the lift distribution is approximately elliptical across th span.
This gives the lowest induced drag for a given span, but not the lowest bending moment (structural weight) for a given level of drag If the outer wing loading is significantly reduced the bending moment is reduced with little change in drag. This improves the drag/bending moment ratio The outer low loaded section is about 25% of the span, but may be greater or less depending upon the particular application.
Figure 1 A. Shows the lift approximate lift distribution of the Kudowa wing.
B. Shows the approximate lift distribution of a standard wing.
(the area under the curves are equal).
The significant factor is that the lift on the outer wing is significantly reduced compared with the conventional wing.

Claims (4)

  1. CLAIMS An off loaded outer wing reduces the bending moment allowing greater span and reduced drag.
  2. 2 The drag is reduced compared to a normal wing of similar bending moment.
  3. 3 The bending moment is reduced compared to a normal wing of similar span.
  4. 4 To be effective there is a significant difference in the lift between the inner and outer sections of the wing.
GB0912603A 2009-07-29 2009-07-29 Wing Withdrawn GB2472766A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0912603A GB2472766A (en) 2009-07-29 2009-07-29 Wing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0912603A GB2472766A (en) 2009-07-29 2009-07-29 Wing

Publications (2)

Publication Number Publication Date
GB0912603D0 GB0912603D0 (en) 2009-08-26
GB2472766A true GB2472766A (en) 2011-02-23

Family

ID=41058240

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0912603A Withdrawn GB2472766A (en) 2009-07-29 2009-07-29 Wing

Country Status (1)

Country Link
GB (1) GB2472766A (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2043572A (en) * 1979-03-09 1980-10-08 Dornier Gmbh Aerodynamic lateral flow body, for example, an airfoil
US4611773A (en) * 1982-12-30 1986-09-16 The Boeing Company Tapered thickness-chord ratio wing
WO1998056654A1 (en) * 1997-06-13 1998-12-17 The Boeing Company Blunt-leading-edge raked wingtips
US6722615B2 (en) * 2001-04-09 2004-04-20 Fairchild Dornier Gmbh Wing tip extension for a wing

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2043572A (en) * 1979-03-09 1980-10-08 Dornier Gmbh Aerodynamic lateral flow body, for example, an airfoil
US4611773A (en) * 1982-12-30 1986-09-16 The Boeing Company Tapered thickness-chord ratio wing
WO1998056654A1 (en) * 1997-06-13 1998-12-17 The Boeing Company Blunt-leading-edge raked wingtips
US6722615B2 (en) * 2001-04-09 2004-04-20 Fairchild Dornier Gmbh Wing tip extension for a wing

Also Published As

Publication number Publication date
GB0912603D0 (en) 2009-08-26

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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)