Volume 29 Issue 5
May  2014
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2014  >  (5): 1105-1111
ZHANG Qing-feng, XIONG Ke, LI Wei, CHEN Shuang. Numerical simulation on morphing winglets for its drag reduction mechanisms[J]. Journal of Aerospace Power, 2014, (5): 1105-1111.
Citation: ZHANG Qing-feng, XIONG Ke, LI Wei, CHEN Shuang. Numerical simulation on morphing winglets for its drag reduction mechanisms[J]. Journal of Aerospace Power, 2014, (5): 1105-1111.
shu

Numerical simulation on morphing winglets for its drag reduction mechanisms

  • 1. Flight Technology College, Civil Aviation Flight University of China, Guanghan Sichuan 618307, China;

  • 2. College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 3. State Key Laboratory of Mechanics and Control of Mechanical Structures, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 4. School of Air Transportion, Shanghai University of Engineering Science, Shanghai 201620, China;

  • 5. Aircraft Repair and Overhaul Plant, Civil Aviation Flight University of China, Guanghan Sichuan 618307, China

  • Received Date: 2013-06-16
  • Publish Date: 2014-05-28
    Abstract
  • The most critical geometric parameters of winglets in drag reduction efficiency were summarized. Then the numerical simulation method was utilized to reveal the optimal range of these parameters, which is the theoretical basis of morphing winglet design. The advantages and disadvantages of morphing winglets in aerodynamic performance, aerodynamic load distribution and wingtip vortices were discussed compared with traditional winglets. The results show that morphing winglets can increase the drag reduction efficiency by 2.2% compared with traditional winglets and weaken the wingtip vortices by 15% in the takeoff phase of flight. It is beneficial to enhance the fuel efficiency of aircraft and the airport spatial security. However, morphing winglets increase the bending moment at the wing root. For this reason, aircraft designers have to strik a balance between the aerodynamic benefits and the structural disadvantages in morphing winglet designs.

     

    • FullText(HTML)
  • loading
    • References(15)
  • [1]
    Anderson J D.Introduction to flight[M].5th ed.New York:McGraw-Hill Science, 2004:31-33.
    [2]
    马汉东, 崔尔杰.大型飞机阻力预示与减阻研究[J].力学与实践, 2007, 29(2):1-8. MA Handong, CUI Erjie.Drag prediction and reduction for civil transportation aircraft[J].Mechanics in Engineering, 2007, 29(2):1-8.(in Chinese)
    [3]
    Whitcomb R T.A design approach and selected wind tunnel results at high subsonic speeds for wing-tip mounted winglets[R].NASA TN D-8260, 1976.
    [4]
    Flechner S G, Jacobs P F, Whitcomb R T.A high subsonic speed wind tunnel investigation of winglets on a representative second-generation jet transport wing[R].NASA TN D-8264, 1976.
    [5]
    江永泉.飞机翼梢小翼设计[M].北京:航空工业出版社, 2009:19-20.
    [6]
    Bourdin P, Gatto A, Friswell M I.Aircraft control via variable cant-angle winglets[J].Journal of Aircraft, 2008, 45(2):414-423.
    [7]
    Ursache N M, Melin T, Isikveren A T, et al.Morphing winglets for aircraft multi-phase improvement[R].AIAA-2007-7813, 2007.
    [8]
    Gatto A, Mattioni F, Friswell M I.Experimental investigation of bistable winglets to enhance wing lift takeoff capability[J].Journal of Aircraft, 2009, 46(2):647-655.
    [9]
    Ameri N, Lowenberg M H, Friswell M I.Modeling the dynamic response of a morphing wing with active winglets[R].AIAA-2007-6500, 2007.
    [10]
    Ursache N M, Melin T, Isikveren A T.Technology integration for active poly-morphing winglets development[R].Smart Materials, Adaptive Structures and Intelligent Systerms, SMASIS-2008-496, 2008.
    [11]
    Catalano F M, Ceron-Munoz H D.Experimental analysis of aerodynamics characteristics of adaptive multi-winglets[R].AIAA-2005-1231, 2005.
    [12]
    Shelton A, Tomar A, Prasad J V R, et al.Active multiple winglets for improved UAV performance[R].AIAA-2004-4968, 2004.
    [13]
    Sankrithi M, Fromme J B.Controllable winglets:US, US 2008/0308683 A1[P].2008-12-18.
    [14]
    Ishimitsu K K.Design and analysis of winglets for military aircraft[R].Air Force Flight Dynamics Laboratory AFFDL-TR-76-6, 1976.
    [15]
    Ishimitsu K K.Design and analysis of winglets for military aircraft:Phase Ⅱ[R].Air Force Flight Dynamics Laboratory AFFDL-TR-77-23, 1977.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(1013.0KB)
    XML

    Article Metrics

    Article views (1608) PDF downloads(983) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return