GB488942A - Improvements in or connected with aerofoil surfaces for aircraft - Google Patents

Improvements in or connected with aerofoil surfaces for aircraft

Info

Publication number
GB488942A
GB488942A GB1397/37A GB139737A GB488942A GB 488942 A GB488942 A GB 488942A GB 1397/37 A GB1397/37 A GB 1397/37A GB 139737 A GB139737 A GB 139737A GB 488942 A GB488942 A GB 488942A
Authority
GB
United Kingdom
Prior art keywords
aerofoil
passage
wing
chord
aircraft
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
GB1397/37A
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.)
GKN Aerospace Services Ltd
Original Assignee
Vickers Aviation 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 Vickers Aviation Ltd filed Critical Vickers Aviation Ltd
Priority to GB1397/37A priority Critical patent/GB488942A/en
Publication of GB488942A publication Critical patent/GB488942A/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
    • 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
    • Y02T50/30—Wing lift efficiency

Landscapes

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

Abstract

488,942. Controlling aircraft. VICKERS (AVIATION), Ltd., and ELLIS, D. L. Jan. 16, 1937, No. 1397. [Class 4] An aerofoil surface for aircraft has openings in its upper and lower surfaces communicating with each other by a passage or passages combined with a separately formed member spaced beneath the aerofoil and shaped to form a convergent-divergent passage between it and the aerofoil, the member extending for a part only of the chord of the aerofoil and being so located that the point of minimum depth of the passage is situated directly beneath the opening in the lower surface. As shown, an auxiliary aerofoil a extends for 25 per cent only of the chord of the aerofoil b and is disposed beneath a passage d. The aerofoil a may be retracted into the recess e. In a modification, the passage f, g, Fig. 2, connects the wing surfaces and the aerofoil a is disposed nearer the leading edge of the wing. In a further modification, the passage g terminates in the rear edge of an aerofoil provided with a flap which in its normal position closes the passage. The auxiliary aerofoil may be disposed at any point on the chord of the main wing and may be adjustable to vary the size of the passage. The size of the passage through the wing may be adjustable.
GB1397/37A 1937-01-16 1937-01-16 Improvements in or connected with aerofoil surfaces for aircraft Expired GB488942A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1397/37A GB488942A (en) 1937-01-16 1937-01-16 Improvements in or connected with aerofoil surfaces for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1397/37A GB488942A (en) 1937-01-16 1937-01-16 Improvements in or connected with aerofoil surfaces for aircraft

Publications (1)

Publication Number Publication Date
GB488942A true GB488942A (en) 1938-07-18

Family

ID=9721284

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1397/37A Expired GB488942A (en) 1937-01-16 1937-01-16 Improvements in or connected with aerofoil surfaces for aircraft

Country Status (1)

Country Link
GB (1) GB488942A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2631794A (en) * 1947-07-22 1953-03-17 Douglas K Warner Airfoil nose flap arrangement
US2809793A (en) * 1947-07-22 1957-10-15 Douglas K Warner High lift airfoil system
DE1078875B (en) * 1957-07-03 1960-03-31 Flugzeugwerke Dresden Veb Body flowed over with slits that lead from one side of the flow to the other
FR2555676A1 (en) * 1983-11-24 1985-05-31 Messerschmitt Boelkow Blohm METHOD FOR SUBJECTING THE DETACHED LAMINARY BOUNDARY LAYER TO A STABILIZING INFLUENCE
GB2285669A (en) * 1994-01-13 1995-07-19 Short Brothers Plc Boundary layer control in aerodynamic structures
FR2850353A1 (en) * 2003-01-29 2004-07-30 Const Aeronautiques Du Nord Es Air flow turbulence modulator comprises duct through rear part of wing and suction unit beneath it to draw air flow from upper surface
CN117446152A (en) * 2023-12-22 2024-01-26 中国航空工业集团公司西安飞机设计研究所 Cracking type control surface structure and aircraft

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2631794A (en) * 1947-07-22 1953-03-17 Douglas K Warner Airfoil nose flap arrangement
US2809793A (en) * 1947-07-22 1957-10-15 Douglas K Warner High lift airfoil system
DE1078875B (en) * 1957-07-03 1960-03-31 Flugzeugwerke Dresden Veb Body flowed over with slits that lead from one side of the flow to the other
FR2555676A1 (en) * 1983-11-24 1985-05-31 Messerschmitt Boelkow Blohm METHOD FOR SUBJECTING THE DETACHED LAMINARY BOUNDARY LAYER TO A STABILIZING INFLUENCE
GB2285669A (en) * 1994-01-13 1995-07-19 Short Brothers Plc Boundary layer control in aerodynamic structures
US5743493A (en) * 1994-01-13 1998-04-28 Short Brothers Plc Boundary layer control in aerodynamic low drag structures
GB2285669B (en) * 1994-01-13 1998-06-10 Short Brothers Plc Boundary layer control in aerodynamic low drag structures
FR2850353A1 (en) * 2003-01-29 2004-07-30 Const Aeronautiques Du Nord Es Air flow turbulence modulator comprises duct through rear part of wing and suction unit beneath it to draw air flow from upper surface
CN117446152A (en) * 2023-12-22 2024-01-26 中国航空工业集团公司西安飞机设计研究所 Cracking type control surface structure and aircraft

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