共轴刚性旋翼悬停流场的PIV风洞试验研究
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摘要
使用粒子图像测速(Particle image velocity,PIV)技术对2 m直径共轴刚性旋翼悬停流场进行了风洞试验研究。在所搭建的共轴刚性旋翼试验台上,对1 100 r/min和1 860 r/min两种转速,8°和10°两种总距下的共轴刚性旋翼流场进行了测量,并测量了单独上旋翼相同状态下的流场。通过对试验数据进行处理,得到了不同状态下桨尖涡的脱落轨迹以及流场速度矢量图。同时通过对比分析,研究了共轴刚性旋翼之间的气动干扰现象,并指出了上旋翼桨尖涡尾迹通过下旋翼桨盘时的"二次收缩"效应。
The flowfield of ?2 m rigid coaxial rotor in hovering state were measured in wind tunnel based on particle image velocity(PIV) technique. The test condition with rotational speeds of 1 100 r/min and 1 860 r/min,collective pitches of 8° and 10° were measured on the test rigid coaxial rotor stand. Meanwhile,the isolate upper rotor under the same condition were measured for comparison. The trajectory of tip vortex and the distribution of velocity vector were obtained. Furthermore,the aerodynamic interaction between the upper rotor and the lower rotor were investigated,and the"secondary contraction effect"of the vortex wake of the upper rotor was observed when it passed through the disk of the lower rotor.
The flowfield of ?2 m rigid coaxial rotor in hovering state were measured in wind tunnel based on particle image velocity(PIV) technique. The test condition with rotational speeds of 1 100 r/min and 1 860 r/min,collective pitches of 8° and 10° were measured on the test rigid coaxial rotor stand. Meanwhile,the isolate upper rotor under the same condition were measured for comparison. The trajectory of tip vortex and the distribution of velocity vector were obtained. Furthermore,the aerodynamic interaction between the upper rotor and the lower rotor were investigated,and the"secondary contraction effect"of the vortex wake of the upper rotor was observed when it passed through the disk of the lower rotor.
引文
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[9]黄水林,林永峰,黄建萍,等.基于PIV技术的纵列式双旋翼尾迹特性实验研究[J].空气动力学学报,2012,30(3):334-339.HUANG Shuilin,LIN Yongfeng,HUANG Jianping,et al.Experimental investigation on the wake characteristics of tandem twin rotors[J].Acta Aerodynamica Sinica,2012,30(3):334-339.
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[14]于世美,邓彦敏.共轴式双旋翼悬停流场的水洞PIV测量[J].航空动力学报,2007,22(11):1852-1857.YU Shimei,DENG Yanmin.PIV measurement of water tunnel for the flow field of a hovering coaxial rotor[J].Journal of Aerospace Power,2007,22(11):1852-1857.
[15]马杨超,于世美,邓彦敏.共轴式双旋翼悬停诱导速度场的PIV实验研究[J].实验流体力学,2012,26(1):16-20.MA Yangchao,YU Shimei,DENG Yanmin.PIV experimental investigation of coaxial rotor's induced velocity field in hover[J].Journal of Experiments in Fluid Mechanics,2012,26(1):16-20.
[16]唐正飞,高正.共轴双旋翼与单旋翼悬停流场实验测量值的对比[J].南京航空航天大学学报,1997,29(6):627-632.TANG Zhengfei,GAO Zheng.Comparison of experimental data for the coaxial rotor and single rotor flowfield in hovering[J].Journal of Nanjing University of Aeronautics&Astronautics,1997,29(6):627-632.
[2]JAMES S.Experimental investigation of rotor vortex wakes in descent[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit.Reno USA:AIAA,2004:297-307.
[3]GREEN R B,GILLIES E A,BROWN R E.The flow field around a rotor in axial descent[J].Journal of Fluid Mechanics,2005,534:237-261.
[4]LANDGREBE A J.The wake geometry of a hovering helicopter and its influence on rotor performance[J].Journal of the American Helicopter Society,1972,17(4):3-15.
[5]杨永东,武杰.悬停旋翼桨尖涡的试验研究[J].实验流体力学,2008,22(3):36-39.YANG Yongdong,WU Jie.Investigation of hovering rotor tip vortex[J].Journal of Experiments in Fluid Mechanics,2008,22(3):36-39.
[6]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 measuring wake geometry for helicopter rotors in forward flight[J].Journal of Experiments in Fluid Mechanics,2010,24(4):29-32.
[7]刘平安,林永峰,陈垚峰,等.旋翼悬停状态桨尖涡测量方法研究[J].实验流体力学,2017,31(4):39-44.LIU Ping’an,LIN Yongfeng,CHEN Yaofeng,et al.Blade tip vortex measurements of a hovering rotor[J].Journal of Experiments in Fluid Mechanics,2017,31(4):39-44.
[8]李春华,曹金华,吴裕平.直升机旋翼流场特性PIV试验分析[J].直升机技术,2012(1):6-10.LI Chunhua,CAO Jinhua,WU Yuping.PIV experimental investigation on flow field for helicopter rotor[J].Helicopter Technique,2012(1):6-10.
[9]黄水林,林永峰,黄建萍,等.基于PIV技术的纵列式双旋翼尾迹特性实验研究[J].空气动力学学报,2012,30(3):334-339.HUANG Shuilin,LIN Yongfeng,HUANG Jianping,et al.Experimental investigation on the wake characteristics of tandem twin rotors[J].Acta Aerodynamica Sinica,2012,30(3):334-339.
[10]BURGESS R K.The ABCTM rotor-A historical perspective[C]//The 60th Annual Forum of the American Helicopter Scoiety,International.Baltimore,USA:[s.n.],2004.
[11]PAGLINO V M,BENO E A.Full-scale wind tunnel investigation of the advancing blade concept rotor system:AD 734338[R].Fort Eustis,USA:USAAVLABS,1971.
[12]FELKER F F.Performance and loads data from a wind tunnel test of a full-scale,coaxial,hingeless rotor helicopter:NASA/TM-81329[R].USA:NASA,1981.
[13]LORBER P,LAW G,O'NEILL J,et al.Overview of S-97 RAIDER scale model tests[C]//The AHS72th Annual Forum.West Palm Beach,USA:[s.n.],2016.
[14]于世美,邓彦敏.共轴式双旋翼悬停流场的水洞PIV测量[J].航空动力学报,2007,22(11):1852-1857.YU Shimei,DENG Yanmin.PIV measurement of water tunnel for the flow field of a hovering coaxial rotor[J].Journal of Aerospace Power,2007,22(11):1852-1857.
[15]马杨超,于世美,邓彦敏.共轴式双旋翼悬停诱导速度场的PIV实验研究[J].实验流体力学,2012,26(1):16-20.MA Yangchao,YU Shimei,DENG Yanmin.PIV experimental investigation of coaxial rotor's induced velocity field in hover[J].Journal of Experiments in Fluid Mechanics,2012,26(1):16-20.
[16]唐正飞,高正.共轴双旋翼与单旋翼悬停流场实验测量值的对比[J].南京航空航天大学学报,1997,29(6):627-632.TANG Zhengfei,GAO Zheng.Comparison of experimental data for the coaxial rotor and single rotor flowfield in hovering[J].Journal of Nanjing University of Aeronautics&Astronautics,1997,29(6):627-632.