动力失效对起飞纵向气动特性影响数值研究
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摘要
研究民用飞机动力失效对飞机起飞阶段纵向气动特性的影响规律及其机理,对保证飞机有效操纵和安全飞行具有重要意义。采用在点对点多块结构化网格系统上求解三维可压缩雷诺平均N-S方程的数值方法,研究发动机动力失效对某民用飞机起飞构型纵向气动特性的影响。通过DLR-F11模型验证研究方法对民用飞机高升力构型气动特性的预测能力;针对安装动力短舱的某翼吊涡扇发动机民用飞机起飞构型,通过对比其发动机在正常工况和失效时飞机气动特性的差异,得出动力失效对飞机纵向气动特性的影响规律及机理。结果表明:动力失效后,不但溢流效应会使飞机阻力系数增大;还会导致发动机进、排气特性较正常工作状态明显不同,恶化短舱附近流场,对飞机的升力、失速特性带来不利影响。
It is important to study the influence and mechanism for longitudinal aerodynamic characteristics of a civil aircraft due to engine failure at takeoff stage.It is of important significance to ensure the effective operation and safe flight of the aircraft.Three-dimensional compressible RANS equations on a point-to-point multi-block structured grid are used to investigate the effects of engine failure on longitudinal aerodynamic characteristics of a civil aircraft take-off configuration.Firstly,the DLR-F11 standard model is computed to validate the reliability of the research method.Results show that the computational predictions agree well with the experiment results,so that the research method could be used to predict flow field of a complex civil transport aircraft configuration with high lift device.Secondly,the effects of engine failure on longitudinal aerodynamic characteristics of a civil transport aircraft are investigated.The results show that engine failure not only makes the drag coefficient increasing obviously,but also affects the lift coefficient,pitching moment and stall characteristics adversely.
It is important to study the influence and mechanism for longitudinal aerodynamic characteristics of a civil aircraft due to engine failure at takeoff stage.It is of important significance to ensure the effective operation and safe flight of the aircraft.Three-dimensional compressible RANS equations on a point-to-point multi-block structured grid are used to investigate the effects of engine failure on longitudinal aerodynamic characteristics of a civil aircraft take-off configuration.Firstly,the DLR-F11 standard model is computed to validate the reliability of the research method.Results show that the computational predictions agree well with the experiment results,so that the research method could be used to predict flow field of a complex civil transport aircraft configuration with high lift device.Secondly,the effects of engine failure on longitudinal aerodynamic characteristics of a civil transport aircraft are investigated.The results show that engine failure not only makes the drag coefficient increasing obviously,but also affects the lift coefficient,pitching moment and stall characteristics adversely.
引文
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[2]贾洪印,邓有奇,马明生,等.民用大飞机动力影响数值模拟研究[J].空气动力学学报,2012,30(6):725-730.Jia Hongyin,Deng Youqi,Ma Mingsheng,et al.Numerical investigation of the powered effects on civil aircraft[J].Acta Aerodynamica Sinica,2012,30(6):725-730.(in Chinese)
[3]乔磊,白俊强,华俊,等.大涵道比翼吊发动机喷流气动干扰研究[J].空气动力学学报,2014,32(4):433-438.Qiao Lei,Bai Junqiang,Hua Jun,et al.Interference effects of wing-mounted high bypass ratio nacelle with engine power[J].Acta Aerodynamica Sinica,2014,32(4):433-438.(in Chinese)
[4]谭兆光,陈迎春,李杰,等.机体/动力装置一体化分析中的动力影响效应数值模拟[J].航空动力学报,2009,24(8):1766-1772.Tan Zhaoguang,Chen Yingchun,Li Jie,et al.Numerical simulation method for the powered effects in airframe/propulsion integration analysis[J].Journal of Aerospace Power,2009,24(8):1766-1772.(in Chinese)
[5]张美红,王志栋.CFD技术在带动力飞机气动设计中的应用[J].民用飞机设计与研究,2004(4):52-55.Zhang Meihong,Wang Zhidong.The application of CFD in powered aircraft aerodynamic design[J].Civil Aircraft Design and Research,2004(4):52-55.(in Chinese)
[6]Chen H C,Yu N J,Rubbert P E.Flow simulations for general nacelle configurations using Euler equations[C].AIAA-83-0539,1983.
[7]Chuck C,Hsiao E,Colehour J,et al.Naviers-Stokes calulations of under wing turbofan nacelles[R].AIAA-98-2734,1998.
[8]胡宁,郝璇,苏诚,等.风洞阻塞度对起落架气动噪声测量影响的数值模拟研究[J].空气动力学学报,2015,33(2):225-231.Hu Ning,Hao Xuan,Su Cheng,et al.Numerical investigation to wind-tunnel-blockage effects on aerodynamic noise measurements of a landing gear[J].Acta Aerodynamica Sinica,2015,33(2):225-231.
[9]Menter F R.Zonal two-equation k-ωturbulence models for aerodynamic flows[R].AIAA-93-2906,1993.
[10]Thomas J L.An implicit multigrid scheme for hypersonic strong-interaction flowfields[J].Communications in Applied Numerical Methods,1992,8(9):683-693.
[11]郭少杰,王豪杰,李杰.外吹式襟翼动力增升数值模拟方法研究[J].航空工程进展,2010,1(1):49-54.Guo Shaojie,Wang Haojie,Li Jie.Numerical simulating method for powered high-lift flow[J].Advances in Aeronautical Science and Engineering,2010,1(1):49-54.(in Chinese)
[12]Pulliam T H.High-lift OVERFLOW analysis of the DLRF11wind tunnel model[R].AIAA-2014-2697,2014.
[13]Rudnik R.Experimental analysis of separation and transition phenomena for the DLR-F11high lift configuration[J].AIAA-2013-3035,2013.
[14]Rumsey C L,Slotnick J P.Overview and summary of the second AIAA high lift prediction workshop[J].Journal of Aircraft,2014,52(4):747-756.
[15]Gopalakrishna N,Balakrishnan N.High lift flow computations using the code HiFun[R].AIAA-2014-2569,2014.
[16]Kedar C,Michel R,Jeffrey M,et al.Finite element flow simulations of the EUROLIFT DLR-F11high lift configuration[J].Eprint Arxiv,2014(3):749-752.
[17]Jeremy H,Prashanth S,Deryl S.Numerical simulation of DLR-F11 high lift configuration from HiLiftPW-2 using STAR-CCM+[C].AIAA-2014-0914,2014.