BLI效应下整流罩设计对翼型气动特性的影响

项洋; 吴江浩; 张艳来

doi:10.13700/j.bh.1001-5965.2015.0802

BLI效应下整流罩设计对翼型气动特性的影响

doi: 10.13700/j.bh.1001-5965.2015.0802

北京航空航天大学交通科学与工程学院, 北京 100083

详细信息

作者简介:
项洋男,博士研究生。主要研究方向:飞机空气动力学。E-mail:xiangyangbuaa@buaa.edu.cn;吴江浩男,博士,教授,博士生导师。主要研究方向:飞机空气动力学、仿生流体力学与飞行力学。Tel.:010-82316627 E-mail:buaawjh@buaa.edu.cn;张艳来男,博士,讲师,硕士生导师。主要研究方向:飞机空气动力学。E-mail:zhangyanlai@buaa.edu.cn

通讯作者:
吴江浩,Tel.:010-82316627 E-mail:buaawjh@buaa.edu.cn

中图分类号: V221.3
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出版历程
- 收稿日期: 2015-12-03
- 网络出版日期: 2016-05-20

Effects of cowling design on aerodynamic performance of airfoil with BLI

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

摘要

摘要: 边界层吸入(BLI)效应对飞行器气动特性的影响比较显著,而整流罩的设计会进一步影响BLI效应下的翼型气动特性。为了揭示BLI效应下整流罩的主要设计参数对翼型气动特性的影响及其原因,本文采用计算流体力学(CFD)和Morris敏感度分析相结合的方法对该问题进行了详细研究,得到了整流罩主要设计参数对翼型气动特性的敏感度排序和耦合影响程度排序;对敏感度较高和耦合影响较大的参数进行了流动分析。结果表明:在巡航和起飞2种状态下,对气动系数影响相对较大的设计参数是整流罩最大厚度和进气边界弦向位置,整流罩最大厚度对翼型气动特性影响的主要原因是整流罩背风面会发生局部分离,且其还会改变阻力-流量系数曲线的趋势;整流罩最大厚度和进气边界弦向位置对翼型气动特性的耦合影响作用较强。
- 翼身融合 /
- 边界层吸入(BLI) /
- 计算流体力学(CFD) /
- 耦合布局 /
- 敏感度分析
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.
- blended wing body /
- boundary layer ingestion (BLI) /
- computational fluid dynamics (CFD) /
- coupled configuration /
- sensitivity analysis

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参考文献(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.