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GB1404153A - Aircraft wings - Google Patents

Aircraft wings

Info

Publication number
GB1404153A
GB1404153A GB5409872A GB5409872A GB1404153A GB 1404153 A GB1404153 A GB 1404153A GB 5409872 A GB5409872 A GB 5409872A GB 5409872 A GB5409872 A GB 5409872A GB 1404153 A GB1404153 A GB 1404153A
Authority
GB
United Kingdom
Prior art keywords
wing
slot
spoiler
nov
trailing edge
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.)
Expired
Application number
GB5409872A
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of GB1404153A publication Critical patent/GB1404153A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/146—Adjustable control surfaces or members, e.g. rudders forming slots at an other wing location than the rear or the front
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
    • 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)
  • Body Structure For Vehicles (AREA)
  • Air-Flow Control Members (AREA)
  • Toys (AREA)

Abstract

1404153 Aircraft wing MITSUBISHI JUKOGYO KK 22 Nov 1972 [24 Nov 1971] 54098/72 Heading B7G [Also in Division F2] An aircraft wing 1 is provided with a spoiler 2 located in a slot 4 through the wing and mounted at 5 for upward pivoting, and means located in the slot for causing vortices 10 in air flowing from the underside of the wing through the slot when the spoiler 2 is raised. Such means may be a sawtooth edged plate 7 or a plurality of rods (8), Figs. 9-12 (not shown), and may be located on the trailing edge of the spoiler 2 or on the wing 1 to the rear of the slot 4, Figs. 13, 14 (not shown). The wing has a trailing edge flap 3, and the effect of the vortexproducing means is to delay boundary-layer separation when the flap is deployed.
GB5409872A 1971-11-24 1972-11-22 Aircraft wings Expired GB1404153A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP46093591A JPS5211520B2 (en) 1971-11-24 1971-11-24

Publications (1)

Publication Number Publication Date
GB1404153A true GB1404153A (en) 1975-08-28

Family

ID=14086525

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5409872A Expired GB1404153A (en) 1971-11-24 1972-11-22 Aircraft wings

Country Status (5)

Country Link
JP (1) JPS5211520B2 (en)
DE (1) DE2253877C3 (en)
FR (1) FR2160854B1 (en)
GB (1) GB1404153A (en)
SE (1) SE397506B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2176570A (en) * 1985-06-14 1986-12-31 Messerschmitt Boelkow Blohm Vortex generator and/or boundary-layer separator arrangements
US8231084B2 (en) 2008-06-09 2012-07-31 Airbus Operations Limited Aircraft wing
US20120286101A1 (en) * 2007-05-25 2012-11-15 Makoto Hirai High-lift device, wing, and noise reduction structure for high-lift device
RU2524289C1 (en) * 2013-02-19 2014-07-27 Юлия Алексеевна Щепочкина Railway car
CN114408158A (en) * 2022-03-03 2022-04-29 中国商用飞机有限责任公司 Flow perturbation device and operation method thereof

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5131498A (en) * 1974-09-10 1976-03-17 Kawasaki Heavy Ind Ltd Hikikomikanona borutetsukusujenereeta
DE2855016C2 (en) * 1978-12-20 1984-05-03 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Flap arrangement for aircraft
US5294080A (en) * 1993-02-08 1994-03-15 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Lift enhancing tabs for airfoils
US9193436B2 (en) 2013-07-03 2015-11-24 The Boeing Company Flow control structure and associated method for controlling attachment with a control surface

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2176570A (en) * 1985-06-14 1986-12-31 Messerschmitt Boelkow Blohm Vortex generator and/or boundary-layer separator arrangements
US20120286101A1 (en) * 2007-05-25 2012-11-15 Makoto Hirai High-lift device, wing, and noise reduction structure for high-lift device
US9010692B2 (en) * 2007-05-25 2015-04-21 Mitsubishi Heavy Industries, Ltd. High-lift device, wing, and noise reduction structure for high-lift device
US8231084B2 (en) 2008-06-09 2012-07-31 Airbus Operations Limited Aircraft wing
RU2524289C1 (en) * 2013-02-19 2014-07-27 Юлия Алексеевна Щепочкина Railway car
CN114408158A (en) * 2022-03-03 2022-04-29 中国商用飞机有限责任公司 Flow perturbation device and operation method thereof
CN114408158B (en) * 2022-03-03 2024-02-02 中国商用飞机有限责任公司 Turbulent flow device and operation method thereof

Also Published As

Publication number Publication date
FR2160854B1 (en) 1977-08-05
DE2253877B2 (en) 1975-03-06
JPS4858600A (en) 1973-08-16
DE2253877A1 (en) 1973-06-07
FR2160854A1 (en) 1973-07-06
SE397506B (en) 1977-11-07
JPS5211520B2 (en) 1977-03-31
DE2253877C3 (en) 1975-10-16

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
746 Register noted 'licences of right' (sect. 46/1977)
PE20 Patent expired after termination of 20 years