迷你翼梢小翼增升减阻效应
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摘要
选取某窄体客机的翼梢小翼为研究对象,采用Spalart-Allmaras模型对无翼梢小翼、全尺寸翼梢小翼和迷你翼梢小翼3种机翼构型进行数值模拟,通过流场分析和速度分解等手段,研究翼梢小翼的增升减阻机理。结果表明:迷你翼梢小翼有恢复涡核流速、减弱涡流掺混程度和梳理翼梢气流的作用;增升减阻的关键在于迷你翼梢小翼对气流方向的修正;翼梢小翼的局部流动差异会对整体机翼近场造成影响。由于尺寸较小,迷你翼梢小翼能在较大攻角范围内改善传统翼梢小翼的性能,具有一定的实践意义。
Taking the winglet of a narrow-body aircraft as the object,the numerical simulations of three types of wing configuration are carried out using Spalart-Allmaras model,including wingless,full-size winglet and mini winglet. The mechanism of lift enhancement and drag reduction of winglet is studied by means of flow field analysis and velocity decomposition. The results show that the mini winglet can renew the turbulence core velocity,weaken the mixing degree of turbulence and straighten out the wingtip airflow. The key of lift enhancement and drag reduction is the airflow direction correction owing to mini winglet. The local flow difference of winglet will affect the near field of whole wing. Owing to the small size,the mini winglet can improve the performance of traditional winglet in a wide range of attack angle.It has certain practical significance.
Taking the winglet of a narrow-body aircraft as the object,the numerical simulations of three types of wing configuration are carried out using Spalart-Allmaras model,including wingless,full-size winglet and mini winglet. The mechanism of lift enhancement and drag reduction of winglet is studied by means of flow field analysis and velocity decomposition. The results show that the mini winglet can renew the turbulence core velocity,weaken the mixing degree of turbulence and straighten out the wingtip airflow. The key of lift enhancement and drag reduction is the airflow direction correction owing to mini winglet. The local flow difference of winglet will affect the near field of whole wing. Owing to the small size,the mini winglet can improve the performance of traditional winglet in a wide range of attack angle.It has certain practical significance.
引文
[1]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.DOI:10.3969/j.issn.1000-0879.2007.02.001.
[2]A design approach and selected wind-tunnel results at high subsonic speeds for wing-tip mounted winglets:NASA-TN-D-8260-1976[S].
[3]马玉敏,魏剑龙.融合式翼梢小翼减阻效应研究[J].航空工程进展,2018,9(2):245-251.DOI:10.16615/j.cnki.1674-8190.2018.02.014.
[4]杜绵银,崔尔杰,陈培,等.一种新型商用飞机翼梢小翼设计及优化[J].飞机设计,2012,32(2):23-27.
[5]黄江涛,高正红,白俊强,等.基于任意空间属性FFD技术的融合式翼稍小翼稳健型气动优化设计[J].航空学报,2013,34(1):37-45.DOI:10.7527/S1000-6893.2013.0005.
[6]CERON-MUNOZ H D,COSIN R,COIMBRA R F F,et al.Experimental investigation of wing-tip devices on reduction of induced drag[J].Journal of Aircraft,2013,50(2):441-449.DOI:10.2514/1.C031862.
[7]SHKARAYEV S,SU E,ZHAO L F.Aerodynamics of wing with oscillating wingtip flapper[C]//Proceedings of 34th AIAA Applied Aerodynamics Conference.Washington:AIAA,2016.DOI:10.2514/6.2016-3119.
[8]GARMANN D J,VISBAL M R.Interactions of a streamwise-oriented vortex with a finite wing[J].Journal of Fluid Mechanics,2015,767:782-810.DOI:10.1017/jfm.2015.51.
[9]MALIK M R,CROUCH J D,SARIC W S,et al.Application of drag reduction techniques to transport aircraft[C]//Encyclopedia of Aerospace Engineering.Hoboken:John Wiley and Sons Ltd.,2015:eae1013.DOI:10.1002/9780470686652.eae1013.
[10]刘沛清,张雯,郭昊.大型运输机的减阻技术[J].力学与实践,2018,40(2):129-139.DOI:10.6052/1000-0879-17-295.
[11]DJAHID G,POPOV S.Improving the aerodynamics of a transport aircraft wing using a delta planform wingtip leading edge extension[J].Civil Aviation High Technologies,2018,21(1):124-136.DOI:10.26467/2079-0619-2018-21-1-124-136.
[12]陆红雷,刘铁军,马涂亮,等.现代先进翼梢小翼的气动特性分析[J].科技信息,2013(18):375-376.DOI:10.3969/j.issn.1001-9960.2013.18.328.
[13]黄文涛,向阳,王笑,等.基于翼尖涡物理特征的诱导阻力减阻机制实验研究[J].实验流体力学,2017,31(5):53-59.DOI:10.11729/syltlx20160194.
[14]CHURCHFIELD M J,BLAISDELL G A.Numerical simulations of a wingtip vortex in near field[J].Journal of Aircraft,2009,46(1):230-243.DOI:10.2514/1.38086.
[15]DACLES-MARIANI J,BRADSHAW P,CHOW J S,et al.Numerical/experimental study of a wingtip vortex in near field[J].AIAA Journal,1995,33(9):1561-1568.DOI:10.2514/3.12826.
[16]RHEE S H,KIM S E.Efficient engineering prediction of turbulent wing tip vortex flows[J].Computer Modeling in Engineering and Sciences,2010,62(3):291-309.DOI:10.3970/cmes.2010.062.291.
[17]蒋彪,李杰.民机翼梢小翼气动特性数值模拟分析研究[J].航空计算技术,2011,41(1):38-43.DOI:10.3969/j.issn.1671-654X.2011.01.009.
[18]CHIGIER N A,CORSIGLIA V R.Wind-tunnel studies of wing wake turbulence[J].Journal of Aircraft,1972,9(12):820-825.DOI:10.2514/3.59082.
[19]梁益明,姚朝晖,何枫.翼梢小翼若干几何参数对翼尖涡流场的影响研究[J].应用力学学报,2012,29(5):548-552.
[20]余永刚,周铸,黄江涛,等.单通道客机气动标模CHN-T1设计[J].空气动力学学报,2018,36(3):505-513.DOI:10.7638/kqdlxxb-2018.0072.
[2]A design approach and selected wind-tunnel results at high subsonic speeds for wing-tip mounted winglets:NASA-TN-D-8260-1976[S].
[3]马玉敏,魏剑龙.融合式翼梢小翼减阻效应研究[J].航空工程进展,2018,9(2):245-251.DOI:10.16615/j.cnki.1674-8190.2018.02.014.
[4]杜绵银,崔尔杰,陈培,等.一种新型商用飞机翼梢小翼设计及优化[J].飞机设计,2012,32(2):23-27.
[5]黄江涛,高正红,白俊强,等.基于任意空间属性FFD技术的融合式翼稍小翼稳健型气动优化设计[J].航空学报,2013,34(1):37-45.DOI:10.7527/S1000-6893.2013.0005.
[6]CERON-MUNOZ H D,COSIN R,COIMBRA R F F,et al.Experimental investigation of wing-tip devices on reduction of induced drag[J].Journal of Aircraft,2013,50(2):441-449.DOI:10.2514/1.C031862.
[7]SHKARAYEV S,SU E,ZHAO L F.Aerodynamics of wing with oscillating wingtip flapper[C]//Proceedings of 34th AIAA Applied Aerodynamics Conference.Washington:AIAA,2016.DOI:10.2514/6.2016-3119.
[8]GARMANN D J,VISBAL M R.Interactions of a streamwise-oriented vortex with a finite wing[J].Journal of Fluid Mechanics,2015,767:782-810.DOI:10.1017/jfm.2015.51.
[9]MALIK M R,CROUCH J D,SARIC W S,et al.Application of drag reduction techniques to transport aircraft[C]//Encyclopedia of Aerospace Engineering.Hoboken:John Wiley and Sons Ltd.,2015:eae1013.DOI:10.1002/9780470686652.eae1013.
[10]刘沛清,张雯,郭昊.大型运输机的减阻技术[J].力学与实践,2018,40(2):129-139.DOI:10.6052/1000-0879-17-295.
[11]DJAHID G,POPOV S.Improving the aerodynamics of a transport aircraft wing using a delta planform wingtip leading edge extension[J].Civil Aviation High Technologies,2018,21(1):124-136.DOI:10.26467/2079-0619-2018-21-1-124-136.
[12]陆红雷,刘铁军,马涂亮,等.现代先进翼梢小翼的气动特性分析[J].科技信息,2013(18):375-376.DOI:10.3969/j.issn.1001-9960.2013.18.328.
[13]黄文涛,向阳,王笑,等.基于翼尖涡物理特征的诱导阻力减阻机制实验研究[J].实验流体力学,2017,31(5):53-59.DOI:10.11729/syltlx20160194.
[14]CHURCHFIELD M J,BLAISDELL G A.Numerical simulations of a wingtip vortex in near field[J].Journal of Aircraft,2009,46(1):230-243.DOI:10.2514/1.38086.
[15]DACLES-MARIANI J,BRADSHAW P,CHOW J S,et al.Numerical/experimental study of a wingtip vortex in near field[J].AIAA Journal,1995,33(9):1561-1568.DOI:10.2514/3.12826.
[16]RHEE S H,KIM S E.Efficient engineering prediction of turbulent wing tip vortex flows[J].Computer Modeling in Engineering and Sciences,2010,62(3):291-309.DOI:10.3970/cmes.2010.062.291.
[17]蒋彪,李杰.民机翼梢小翼气动特性数值模拟分析研究[J].航空计算技术,2011,41(1):38-43.DOI:10.3969/j.issn.1671-654X.2011.01.009.
[18]CHIGIER N A,CORSIGLIA V R.Wind-tunnel studies of wing wake turbulence[J].Journal of Aircraft,1972,9(12):820-825.DOI:10.2514/3.59082.
[19]梁益明,姚朝晖,何枫.翼梢小翼若干几何参数对翼尖涡流场的影响研究[J].应用力学学报,2012,29(5):548-552.
[20]余永刚,周铸,黄江涛,等.单通道客机气动标模CHN-T1设计[J].空气动力学学报,2018,36(3):505-513.DOI:10.7638/kqdlxxb-2018.0072.