Fluid Mechanics and Flight Mechanics

Study on Influence of Complex Geometry Details on the Aerodynamic Performance of High-lift System

  • QIU Yasong ,
  • BAI Junqiang ,
  • LI Yalin ,
  • ZHOU Tao
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  • 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Ltd., Shanghai 200232, China

Received date: 2011-06-15

  Revised date: 2011-08-30

  Online published: 2012-03-24

Abstract

By numerical simulation, the influence of the main-wing root geometry details, wing-mounted engine nacelle, slat tracks and flap track fairings on the aerodynamic performance of a high-lift system is investigated. The results show that a separated low-power vortex is generated by the wing-root fairing which is left at the main-wing root when the slat is cut, and the aerodynamic performance of the lift system is damaged seriously by this vortex. Cutting most of the wing-root fairing as part of the slat can eliminate the condition needed to generate the separated low-power vortex. Remarkable decrease of the stall angle and maxim lift coefficient is caused by a large size wing-mounted engine nacelle. This is mainly because of the flow mechanism that a large space filled with low-speed fluid above the upper surface of the main wing is generated by the separated fluid which comes from the nacelle upper surface, pylon and the gaps between the pylon and slat. Strong vortices generated by the nacelle strake with proper shape and setting at proper positions can eliminate most of the low-speed fluid and recover part of the aerodynamic performance loss. Low-momentum wake flow generated by the slat tracks mixed with the boundary layer of the main wing causes the loss of the lift. Large fluid separation may be caused by the slat track at high angles of attack, which will result in a remarkable loss of the aerodynamic performance. The flap slot section area may be diminished as a result of the blockage effect of the large size geometry the of flap track fairings, which may cause the high speed flow of the flap slot to move faster, thus blowing away the separation flow on the flap surface.

Cite this article

QIU Yasong , BAI Junqiang , LI Yalin , ZHOU Tao . Study on Influence of Complex Geometry Details on the Aerodynamic Performance of High-lift System[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012 , (3) : 421 -429 . DOI: CNKI:11-1929/V.20111125.1301.002

References

[1] Meredith P T. Viscous phenomena affecting high-lift systems and suggestions for future CFD development. Agard Conference Proceedings 515 High-lift System Aerodynamics. Neuilly Sur Seine France: Specialised Printing Services Limited, 1993,19:1-8.

[2] van der Burg J W, Eliasson P, Delille T, et al. Geometric installation and deformation effects in high-lift flows. AIAA Journal,2009,47(1):60-70.

[3] von Gery H F, Schade N, van der Burg J W, et al. CFD prediction of maximum lift effects on realistic high-lift commercial aircraft configuration. AIAA-2007-4299, 2007.

[4] Rudnik R. Stall behaviour of the eurolift high-lift configurations. AIAA-2008-836, 2008.

[5] Rudnik R, Germain E. Re-No.scaling effects on the EUROLIFT high-lift configurations. AIAA-2007-752, 2007.

[6] Murayama M, Yokokawa Y, Yamamoto K. Validation study of CFD analysis for high-lift systems. Hamburg, Germany: ICAS, 2006.

[7] Rudnik R, von Geyr H F. The european high-lift project EUROLIFT II objectives, approach, and structure. AIAA-2007-4296, 2007.

[8] Wild J, Brezillon J, Amoignon O, et al. Advance high-lift design by numercal methods and wind tunnel verification within European project EOROLIFT II. AIAA-2007-4300, 2007.

[9] Quix H, Schulz M, Quest J, et al. Low speed high lift validation tests within the European project EUROLIFT II. AIAA-2007-4298, 2007.

[10] Eliasson P, Catalano P, Pape M C L, et al. Improved CFD predictions for high lift flows in the European project EUROLIFT II. AIAA-2007-4303, 2007.

[11] Yokokawa Y, Murayama M, Ito T, et al. Experiment and CFD of a high lift configuration civil transport aircraft model. AIAA-2006-3452, 2006.

[12] Yokokawa Y, Murayama M, Kanazaki M, et al. Investigation and improvment of high-lift aerodynamic performence in lowspeed wind tunnel testing. AIAA-2008-350, 2008.

[13] Ito Y, Murayama M, Yamamoto K, et al. Efficient computational fluid dynamics evaluation of small-device locations with automatic local remeshin. AIAA Journal, 2009, 47(5):1270-1276.

[14] Ito T, Yokokawa Y, Ura H, et al. High-lift device testing in JAXA 6.5 m×5.5 m low-speed wind tunnel. AIAA-2006-3643, 2006.

[15] Kato H, Watanabe S, Murayama M, et al. PIV investigation of nacelle chine effects on high-lift system performance. AIAA-2008-240, 2008.

[16] Zhu J. Research on optimal design method based on CFD technology and application of CFD technology in the design of complex configurations. Xi'an: School of Aeronautics, Northwestern Polytechnical University, 2009. (in Chinese) 朱军.应用CFD的优化设计方法及复杂构型设计研究. 西安: 西北工业大学航空学院, 2009.

[17] Menter F R. Zonal two-equation K-W turbulence model for aerodynamic flows. AIAA-1993-2906, 1993.

[18] Catalano P, Amato M. An evaluation of RANS turbulence modelling for aerodynamic applications. Aerospace Science and Technology, 2003, 7: 493-509.

[19] Dang T H. The engine installation of civil aircraft with wing mounted engine configuration.Civil Aircraft Design and Research, 2008(2): 8-14. (in Chinese) 党铁红.翼吊布局民用飞机发动机安装设计. 民用飞机设计与研究, 2008(2): 8-14.

[20] Fang B R. Aerodynamic configuration design of airplane. Beijing: Aviation Industry Press, 1997: 432-433, 1173-1175. (in Chinese) 方宝瑞.飞机气动布局设计.北京:航空工业出版社,1997: 432-433, 1173-1175.
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