翼吊低平尾飞机尾迹测量研究
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摘要
平尾是影响全机纵向力矩的首要部件,翼吊低平尾飞机平尾处的流场受到翼身组合体尾迹的影响。为了摸清尾迹的特点,利用七孔探针测量平尾处的动压及下洗角,得到平尾处流场动压损失以及下洗角随飞机迎角变化的气动特点。结果表明:在接近最大升力系数时,平尾处流场动压损失严重,降低了平尾的气动效率,导致全机的纵向力矩失稳。研究结果对大飞机的气动特性优化工作具有指导意义。
Horizontal tail plane(HTP)is the primary component of aircraft,which influences the longitudinal moment of whole aircraft.The low HTP is affected by the wake of wing-and-fuselage combination in the winghung aircraft.In order to find out the characteristics of the wake,by using the seven hole probe the down wash angle and dynamic pressure are measured.The change of down wash angle and dynamic pressure with the changing of the attack angle can be gained.Results show that the loss of the dynamic pressure of the HTP is severe near the critical angle of attack.It can decrease the efficiency of HTP and cause the instability of longitudinal moment.The research result could be used to optimize the aerodynamic characteristics.
Horizontal tail plane(HTP)is the primary component of aircraft,which influences the longitudinal moment of whole aircraft.The low HTP is affected by the wake of wing-and-fuselage combination in the winghung aircraft.In order to find out the characteristics of the wake,by using the seven hole probe the down wash angle and dynamic pressure are measured.The change of down wash angle and dynamic pressure with the changing of the attack angle can be gained.Results show that the loss of the dynamic pressure of the HTP is severe near the critical angle of attack.It can decrease the efficiency of HTP and cause the instability of longitudinal moment.The research result could be used to optimize the aerodynamic characteristics.
引文
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[2]Richard S Shevell,Roger D Schaufele.Aerodynamic design features of the DC-9[J].Journal of Aircraft,1966,3(6):515-523.
[3]袁红刚,李进学,杨永东,等.前飞状态旋翼尾迹测量试验研究[J].实验流体力学,2010,24(4):29-32.Yuan Honggang,Li Jinxue,Yang Yongdong,et al.Test investigation of wake measurement for rotors in forward flight[J].Journal of Experiments in Fluid Mechanics,2010,24(4):29-32.(in Chinese)
[4]高志鹰,汪建文,韩晓亮.最优S型小翼影响近尾迹流动的PIV测试[J].工程热物理学报,2011,32(12):2044-2047.Gao Zhiying,Wang Jianwen,Han Xiaoliang.PIV experiment on the effect of near wake using horizontal axis wind turbine with optimal ogee tip vane[J].Journal of Engineering Thermophysics,2011,32(12):2044-2047.(in Chinese)
[5]王蕾.七孔探针风洞实验技术研究[D].南京:南京理工大学,2010.Wang Lei.Research of wind tunnel experiment measurement for seven-hole probes[D].Nanjing:Nanjing University of Science and Technology,2010.(in Chinese)
[6]马兴宇,明晓.七孔探针测量剪切流场的误差分析和实验验证[J].空气动力学学报,2012,30(1):57-62,67.Ma Xingyu,Ming Xiao.Experimental research and error analysis on seven-hole probe measurements of shearing flow field[J].Acta Aerodynamica Sinica,2012,30(1):57-62,67.(in Chinese)
[7]周星,杨士普,蒋晓莉.民用飞机大气传感器低速验证试验研究[J].航空工程进展,2013,4(1):43-48.Zhou Xing,Yang Shipu,Jiang Xiaoli.Study on low-speed verification test of atmospheric senors of civil aircraft[J].Advances in Aeronautical Science and Engineering,2013,4(1):43-48.(in Chinese)
[8]杨士普,孙一峰,方阳.民机迎角传感器布局流场分析[C]∥昆明:第九届全国流动显示学术会议论文集,2012.Yang Shipu,Sun Yifeng,Fang Yang.Analysis on the angle of attack sensor layout flow[C]∥Kunming:The ninth National Academic Conference of Flow Visualization,2012.(in Chinese)
[9]Wimpress J K.Predicting the low-speed stall characteristics of the Boeing 747[C].AGARD-CP-102,1972
[10]Ccpany D A.Aerodynamics of high-lift airfoil systems[J].Fluid Dynamics of Aircraft Stalling,1972.
[11]Gratzer L B.Analysis of transport applications for high-lift schemes[C].AGARD LS-43,1970.
[12]周涛,李亚林,鲁岱晓,等.民用飞机失速特性研究[J].民用飞机设计与研究,2012(1):21-26,39.Zhou Tao,Li Yalin,Lu Daixiao,et al.Stall characteristic investigation of civil aircraft[J].Civil Aircarft Design&Research,2012(1):21-26,39.(in Chinese)
[13]艾德·奥波特.运输类飞机的空气动力设计[M].顾诵芬,吴兴世,杨新军,译.上海:上海交通大学出版社,2010.Oport E.Aerodynamic design of transport aircraft[M].Translated by Gu Songfen,Wu Shixing,Yang Xinjun.Shanghai:Shanghai Jiao Tong University Press,2010.(in Chinese)
[14]Burt D O’Laughlin,Lloyd Graham E,John Christiansen.S-3Adevelopment tests[C].AIAA-73-778,1973.
[15]邱亚松,白俊强,李亚林,等.复杂几何细节对增升装置气动性能影响研究[J].航空学报,2012,33(3):421-429.Qiu Yasong,Bai Junqiang,Li Yalin,et al.Study on influence of complex geometry details on the aerodynamic performance of high-lift system[J].Acta Aeronautica et Astronautica Sinica,2012,33(3):421-429.(in Chinese)
[16]叶军科,陈迎春,李亚林,等.民用飞机前缘增升装置气动特性试验研究[J].西北工业大学学报,2011,29(6):904-908.Ye Junke,Chen Yingchun,Li Yalin.Improving further highlift configuration of an airplane model through inboard slat and strake experiments[J].Journal of Northwestern Polytechnical University,2011,29(6):904-908.(in Chinese)
[17]Hiroyuki Kato,Shigeya Watanabe,Mitsuhiro Murayama,et al.PIV investigation of nacelle Chine effects on high-lift system performance[C].AIAA-2008-240,2008.