GB675994A - Improvements in or relating to aircraft wings - Google Patents

Improvements in or relating to aircraft wings

Info

Publication number
GB675994A
GB675994A GB20370/48A GB2037048A GB675994A GB 675994 A GB675994 A GB 675994A GB 20370/48 A GB20370/48 A GB 20370/48A GB 2037048 A GB2037048 A GB 2037048A GB 675994 A GB675994 A GB 675994A
Authority
GB
United Kingdom
Prior art keywords
wing
flap
duct
slots
slot
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
GB20370/48A
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.)
Office National dEtudes et de Recherches Aerospatiales ONERA
Societe Nationale des Constructions Aeronautiques du Sud Oest SNCASO
Original Assignee
Office National dEtudes et de Recherches Aerospatiales ONERA
Societe Nationale des Constructions Aeronautiques du Sud Oest SNCASO
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 Office National dEtudes et de Recherches Aerospatiales ONERA, Societe Nationale des Constructions Aeronautiques du Sud Oest SNCASO filed Critical Office National dEtudes et de Recherches Aerospatiales ONERA
Publication of GB675994A publication Critical patent/GB675994A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C21/00Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/025Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for simultaneous blowing and sucking
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2230/00Boundary layer controls
    • B64C2230/04Boundary layer controls by actively generating fluid flow
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2230/00Boundary layer controls
    • B64C2230/06Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag reduction

Landscapes

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

Abstract

675,994. Controlling aircraft. OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES and SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-OUEST. July 30, 1948 [July 31, 1947; Dec. 22, 1947; July 17, 1948], Nos. 20370/48, 20371/48 and 20372/48. Class 4. An aircraft wing comprises a main section and two pivotal sections whereby the camber of the wing can be varied, the upper surface of said main section defining with the upper surface of one of said pivotal sections an air inlet slot which is variable as said pivotal section is moved to vary the camber of the wing, an airflow discharge slot formed at the upper rear portion of that wing section which lies between the two other sections, a spanwise directed pipe disposed between said air inlet and discharge slots, fluid ejecting means operated through said pipe, a mixing chamber establishing communication between said inlet and discharge slots, and means for supplying fluid under pressure to said ejecting means through said pipe to produce an aspirating effect by the latter for cansing a sheet of air to be drawn in through said inlet slot and discharged through said discharge slot. The device comprises a spanwise duct 10 which may be formed with a rearwardly directed coutinuous slot or may be provided with longitudinally spaced nozzles. The duct is supplied with compressed air or exhaust gases which it ejects into chordwise ducts 9 arranged to eject at 2 through the aperture formed between the trailing edge flaps 6 and the wing. The leading edge of the wing is provided with a nose flap 4 hinged about its lower edge so that when depressed it forms a gap 1 with the wing. The ejector effect of the nozzle 10 creates an airflow through the gap 1 and the duct 9 to control the airflow over the leading edge of the wing and the upper surface of the flap 6. In an alternative arrangement, Fig. 3 (not shown), the duct 10 may comprise two concentric ducts, one supplied with compressed air and the other with exhaust gases. In a further arrangement, Fig. 5 (not shown), the trailing edge of the wing may be provided with a first flap to which is pivoted a second flap. The nozzle 10 and the duct 9 may be installed inside the first flap to draw air from the gap formed between the flap and the wing and eject it through the gap formed between the first and second flaps. The nozzle 10 may be located on the hinge axis of the first flap and arranged to rotate therewith. The Specification as open to inspection under Sect. 91, comprises also a number of embodiments in which a is provided with a single trailing edge flap only and air inlet slots are provided in the fixed upper surface of the wing. A further embodiment is described applied to fuselages and nacelles in which continuous circumferential air inlet and outlet slots are formed in the outer panelling, ejector devices being mounted within the body between the slots. This subject-matter does not appear in the Specification as accepted.
GB20370/48A 1947-07-31 1948-07-30 Improvements in or relating to aircraft wings Expired GB675994A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR675994X 1947-07-31

Publications (1)

Publication Number Publication Date
GB675994A true GB675994A (en) 1952-07-23

Family

ID=9019647

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20370/48A Expired GB675994A (en) 1947-07-31 1948-07-30 Improvements in or relating to aircraft wings

Country Status (1)

Country Link
GB (1) GB675994A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1013174B (en) * 1953-08-12 1957-08-01 Power Jets Res & Dev Ltd Aircraft with lift control devices, e.g. Flaps, on the wing trailing edges
GB2324351A (en) * 1997-04-18 1998-10-21 British Aerospace Reducing drag in aircraft wing assembly
WO2008057065A3 (en) * 2005-08-09 2008-09-25 Boeing Co Lift augmentation system and associated method
EP2955105A1 (en) 2014-06-10 2015-12-16 Instytut Lotnictwa Autonomous active flow control system
CN113071667A (en) * 2021-03-12 2021-07-06 南京航空航天大学 Method for improving wave resistance of amphibious aircraft based on active flow control technology
WO2022128035A1 (en) * 2020-12-15 2022-06-23 Amonyx Aps Airfoil with augmented lift

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1013174B (en) * 1953-08-12 1957-08-01 Power Jets Res & Dev Ltd Aircraft with lift control devices, e.g. Flaps, on the wing trailing edges
GB2324351A (en) * 1997-04-18 1998-10-21 British Aerospace Reducing drag in aircraft wing assembly
US6135395A (en) * 1997-04-18 2000-10-24 British Aerospace Public Limited Company Aircraft wing leading edge high lift device with suction
WO2008057065A3 (en) * 2005-08-09 2008-09-25 Boeing Co Lift augmentation system and associated method
US8033510B2 (en) 2005-08-09 2011-10-11 The Boeing Company Lift augmentation system and associated method
EP2955105A1 (en) 2014-06-10 2015-12-16 Instytut Lotnictwa Autonomous active flow control system
WO2022128035A1 (en) * 2020-12-15 2022-06-23 Amonyx Aps Airfoil with augmented lift
CN113071667A (en) * 2021-03-12 2021-07-06 南京航空航天大学 Method for improving wave resistance of amphibious aircraft based on active flow control technology

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