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Volume 42 Issue 5
May  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(5): 945-952.
XIANG Yang, WU Jianghao, ZHANG Yanlaiet al. Effects of cowling design on aerodynamic performance of airfoil with BLI[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5): 945-952. doi: 10.13700/j.bh.1001-5965.2015.0802(in Chinese)
Citation: XIANG Yang, WU Jianghao, ZHANG Yanlaiet al. Effects of cowling design on aerodynamic performance of airfoil with BLI[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5): 945-952. doi: 10.13700/j.bh.1001-5965.2015.0802(in Chinese)
shu

Effects of cowling design on aerodynamic performance of airfoil with BLI

doi: 10.13700/j.bh.1001-5965.2015.0802

  • School of Transportation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 03 Dec 2015
  • Publish Date: 20 May 2016
    Abstract
  • Boundary layer ingestion (BLI) effect significantly influences aircraft aerodynamic performance. Cowling design further affects aerodynamic performance of airfoil with BLI effect. To clarify the effect and its reason of main cowling design parameters on aerodynamic performance of an airfoil with BLI effect, a detailed study was investigated by computational fluid dynamics (CFD) method and Morris sensitivity analysis method. Sensitivity order and coupled effect order of main parameters on aerodynamic performance were obtained. Flow details of parameters with higher sensitivity and greater coupled effect were analyzed. The results show that in cruise and take-off conditions, the parameters with relatively great impact are cowling maximum thickness and inlet location along the chord direction. The main reason of effects of cowling maximum thickness on aerodynamic performance is that local stall occurs at cowling surface. The variation of cowling maximum thickness also affects the variation trend of plot of drag coefficient to mass flow rate. The coupled effect of cowling maximum thickness and inlet location along the chord direction on aerodynamic performance is relatively great.

     

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    • References(17)
  • [1]
    LIEBECK R H.Design of the blended wing body subsonic transport[J].Journal of Aircraft,2004,41(1):10-25.
    [2]
    QIN N,VAVALLE A,LE MOIGNE A,et al.Aerodynamic considerations of blended wing body aircraft[J].Progress in Aerospace Sciences,2004,40(6):321-343.
    [3]
    LABAN M,ARENDSEN P,ROUWHORST W,et al.A computational design engine for multi-disciplinary optimisation with application to a blended wing body configuration:AIAA-2002-5446[R].Reston:AIAA,2002.
    [4]
    GOHARDANI A S,DOULGERIS G,SINGH R.Challenges of future aircraft propulsion:A review of distributed propulsion technology and its potential application for the all electric commercial aircraft[J].Progress in Aerospace Sciences,2011,47(5):369-391.
    [5]
    KIM H D,BROWN G V,FELDER J L.Distributed turboelectric propulsion for hybrid wing body aircraft[C]//9th International Powered Lift Conference.London:Royal Aeronautical Society,2008:1-11.
    [6]
    HILEMAN J I,SPAKOVSZKY Z S,DRELA M,et al.Airframe design for silent fuel-efficient aircraft[J].Journal of Aircraft,2010,47(3):956-969.
    [7]
    KO A,LEIFSSON L T,SCHETZ J A,et al.MDO of a blended-wing-body transport aircraft with distributed propulsion:AIAA-2003-6732[R].Reston:AIAA,2003.
    [8]
    KO A,SCHETZ J A,MASON W H.Assessment of the potential advantages of distributed-propulsion for aircraft[C]//XVIth International Symposium on Air Breathing Engines (ISABE).Reston:AIAA,2003:71-79.
    [9]
    RODRIGUEZ D L.Multidisciplinary optimization method for designing boundary-layer-ingesting inlets[J].Journal of Aircraft,2009,46(3):883-894.
    [10]
    LUNDBLADH A,GRÖNSTEDT T.Distributed propulsion and turbofan scale effects[C]//ISABE 2005,17th Symposium on Airbreathing Engine.Reston:AIAA,2005.
    [11]
    FELDER J L,KIM H D,BROWN G V.Turboelectric distributed propulsion engine cycle analysis for hybrid-wing-body aircraft:AIAA-2009-1132[R].Reston:AIAA,2009.
    [12]
    闫万方,吴江浩,张艳来.分布式推进关键参数对BWB飞机气动特性影响[J].北京航空航天大学学报,2015,41(6):1055-1065. YAN W F,WU J H,ZHANG Y L.Effects of distributed propulsion crucial variables on aerodynamic performance of blended wing body aircraft[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(6):1055-1065(in Chinese).
    [13]
    WICK A T,HOOKER J R,HARDIN C J.Integrated aerodynamic benefits of distributed propulsion:AIAA-2015-1500[R].Reston:AIAA,2015.
    [14]
    MANTIC^-LUGO V,DOULGERIS G,SINGH R.Computational analysis of the effects of a boundary layer ingesting propulsion system in transonic flow[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2013,227(8):1215-1232.
    [15]
    NICHOLS M R,KEITH A L.Investigation of a systematic group of NACA 1-series cowlings with and without spinners:NACA-Report-950[R].Washington,D.C.:U.S.Government Printing Office,1950.
    [16]
    BARCHE J.Experimental data base for computer program assessment:AGARD-AR-138[R].[S.l.]:AGARD-Report,1979:2002-0843.
    [17]
    MORRIS M D.Factorial sampling plans for preliminary computational experiments[J].Technometrics,1991,33(2):161-174.
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