WO2009106869A3 - Aerodynamic structure with series of shock bumps - Google Patents

Aerodynamic structure with series of shock bumps Download PDF

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Publication number
WO2009106869A3
WO2009106869A3 PCT/GB2009/050150 GB2009050150W WO2009106869A3 WO 2009106869 A3 WO2009106869 A3 WO 2009106869A3 GB 2009050150 W GB2009050150 W GB 2009050150W WO 2009106869 A3 WO2009106869 A3 WO 2009106869A3
Authority
WO
WIPO (PCT)
Prior art keywords
shock
bumps
series
sweep
shock bumps
Prior art date
Application number
PCT/GB2009/050150
Other languages
French (fr)
Other versions
WO2009106869A2 (en
Inventor
Norman Wood
Original Assignee
Airbus Uk Limited
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 Airbus Uk Limited filed Critical Airbus Uk Limited
Priority to BRPI0908342-1A priority Critical patent/BRPI0908342A2/en
Priority to CA2713363A priority patent/CA2713363C/en
Priority to JP2010548185A priority patent/JP2011513114A/en
Priority to CN2009801038126A priority patent/CN101932507A/en
Priority to EP09715558.4A priority patent/EP2250087B1/en
Priority to US12/735,535 priority patent/US9463870B2/en
Publication of WO2009106869A2 publication Critical patent/WO2009106869A2/en
Publication of WO2009106869A3 publication Critical patent/WO2009106869A3/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/04—Influencing air flow over aircraft surfaces, not otherwise provided for by generating shock waves
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/148—Aerofoil profile comprising protuberances, e.g. for modifying boundary layer flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/149—Aerofoil profile for supercritical or transonic flow
    • 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

Abstract

An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock (9) so as to reduce its angle of sweep.
PCT/GB2009/050150 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps WO2009106869A2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
BRPI0908342-1A BRPI0908342A2 (en) 2008-02-29 2009-02-17 Aerodynamic structure with shock protrusion series
CA2713363A CA2713363C (en) 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps
JP2010548185A JP2011513114A (en) 2008-02-29 2009-02-17 Aerodynamic structure with a series of shock bumps
CN2009801038126A CN101932507A (en) 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps
EP09715558.4A EP2250087B1 (en) 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps
US12/735,535 US9463870B2 (en) 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0803727.7 2008-02-29
GBGB0803727.7A GB0803727D0 (en) 2008-02-29 2008-02-29 Aerodynamic structure with series of shock bumps

Publications (2)

Publication Number Publication Date
WO2009106869A2 WO2009106869A2 (en) 2009-09-03
WO2009106869A3 true WO2009106869A3 (en) 2009-10-22

Family

ID=39315678

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2009/050150 WO2009106869A2 (en) 2008-02-29 2009-02-17 Aerodynamic structure with series of shock bumps

Country Status (9)

Country Link
US (1) US9463870B2 (en)
EP (1) EP2250087B1 (en)
JP (1) JP2011513114A (en)
CN (1) CN101932507A (en)
BR (1) BRPI0908342A2 (en)
CA (1) CA2713363C (en)
GB (1) GB0803727D0 (en)
RU (1) RU2010138197A (en)
WO (1) WO2009106869A2 (en)

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GB201002281D0 (en) * 2010-02-11 2010-03-31 Univ Sheffield Apparatus and method for aerodynamic drag reduction
CN101885380B (en) * 2010-07-13 2013-04-24 南京航空航天大学 Asymmetrical design method for leading edge of hypersonic vehicle
US9810099B2 (en) 2015-06-29 2017-11-07 Siemens Energy, Inc. Turbine exhaust cylinder strut strip for shock induced oscillation control
EP3187412B1 (en) * 2015-12-30 2020-03-11 Airbus Defence and Space GmbH Aircraft wing with an adaptive shock control bump
CN107878728B (en) * 2016-09-29 2020-05-05 北京航空航天大学 Wing structure and aircraft
CN106741844A (en) * 2017-01-20 2017-05-31 周朴 The performance improvement method and fluid power plant of a kind of fluid power plant
WO2018165313A1 (en) 2017-03-07 2018-09-13 President And Fellows Of Harvard College Aerodynamic devices for enhancing lift and reducing drag
CN107725477B (en) * 2017-10-10 2019-05-07 北京航空航天大学 A kind of optimization suction surface wave system inhibits the leading edge design method of fan shock wave noise
US11897600B2 (en) * 2019-06-28 2024-02-13 The Boeing Company Trip device for enhancing performance and handling qualities of an aircraft
CN112278238B (en) * 2019-07-26 2022-05-13 香港城市大学深圳研究院 Wing and aircraft that can warp in succession
CN110435876B (en) * 2019-08-26 2020-06-19 中国空气动力研究与发展中心低速空气动力研究所 Coaxial rotor hub fairing with telescopic vortex generator
EP3842336B1 (en) * 2019-12-27 2023-06-28 Bombardier Inc. Variable wing leading edge camber
CN114104281A (en) * 2021-10-29 2022-03-01 西安交通大学 Mute investigation aircraft

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US20060060720A1 (en) * 2004-03-31 2006-03-23 Bogue David R Methods and systems for controlling lower surface shocks

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US20060060720A1 (en) * 2004-03-31 2006-03-23 Bogue David R Methods and systems for controlling lower surface shocks

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Title
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DARGEL G ET AL: "Chapter 21: Assessment of Shock and Boundary Layer Control Concepts for Hybrid Laminar Flow Wing Design", DRAG REDUCTION BY SHOCK AND BOUNDARY LAYER CONTROL. RESULTS OF THE PROJECT EUROSHOCK II, SUPPORTED BY THE EUROPEAN UNION 1996--1999 (BOOK SERIES: NOTES ON NUMERICAL FLUID MECHANICS AND MULTIDISCIPLINARY DESIGN),, vol. 80, 1 January 2002 (2002-01-01), pages 383 - 414, XP009120959, ISBN: 978-3-540-43317-0 *
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Also Published As

Publication number Publication date
CA2713363A1 (en) 2009-09-03
EP2250087A2 (en) 2010-11-17
GB0803727D0 (en) 2008-04-09
US9463870B2 (en) 2016-10-11
WO2009106869A2 (en) 2009-09-03
EP2250087B1 (en) 2013-07-31
CN101932507A (en) 2010-12-29
CA2713363C (en) 2016-05-17
RU2010138197A (en) 2012-04-10
BRPI0908342A2 (en) 2015-07-28
US20100301172A1 (en) 2010-12-02
JP2011513114A (en) 2011-04-28

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