升力偏置对旋翼气动性能的影响
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摘要
采用共轴刚性旋翼的高速直升机是未来旋翼飞行器的发展方向之一,其本质特点即前行侧桨叶会产生升力偏置。为了研究旋翼升力偏置量对刚性旋翼性能的影响,采用自由尾迹方法对采用前行桨叶概念(Advancing blade concept,ABC)的刚性旋翼在不同升力偏置状态下的气动特性进行了计算。通过对计算结果的分析,得到旋翼升力分布、升阻比、阻力特性和功率特性等随升力偏置的变化规律。文中还对前进比μ=0.2,0.4,0.5的计算结果进行了对比分析。结果表明,旋翼升力偏置量的改变能够显著改变旋翼桨盘的升力分布,进而对旋翼气动性能产生重要影响。不同的前进比下,产生旋翼最大前飞升阻比的升力偏置量也会有所不同,μ=0.2时,最大前飞升阻比出现在旋翼升力偏置为20%左右;μ=0.4时,最大前飞升阻比出现在旋翼升力偏置为25%左右,μ=0.5时,最大前飞升阻比出现在旋翼升力偏置为30%左右。
The high speed coaxial helicopter with rigid blades will be the future of rotorcraft,which essential characteristic is the lift-offset of advancing blades. In order to research the influence of lift-offset on the rotor performance,the aerodynamic characteristics of advancing blade concept(ABC)rotor with different lift-offsets are calculated by the rotor free wake method. Through the analysis of the computing results,the effects of liftoffset on rotor lift distribution,lift-drag ratio,drag and power characteristics are obtained. The comparison and analysis of the results of advancing ratios μ=0.2,0.4,0.5 are also conducted. Results indicate that the rotor lift-offset plays a key role in the forward flight performance,thus changing the lift distribution on the rotor.The rotor lift-offset producing maximal lift-drag ratio varies with different advancing ratios. The maximal liftdrag ratio appeares at the lift-offset of about 20%,25%,30%when μ=0.2,0.4,0.5,respectively.
The high speed coaxial helicopter with rigid blades will be the future of rotorcraft,which essential characteristic is the lift-offset of advancing blades. In order to research the influence of lift-offset on the rotor performance,the aerodynamic characteristics of advancing blade concept(ABC)rotor with different lift-offsets are calculated by the rotor free wake method. Through the analysis of the computing results,the effects of liftoffset on rotor lift distribution,lift-drag ratio,drag and power characteristics are obtained. The comparison and analysis of the results of advancing ratios μ=0.2,0.4,0.5 are also conducted. Results indicate that the rotor lift-offset plays a key role in the forward flight performance,thus changing the lift distribution on the rotor.The rotor lift-offset producing maximal lift-drag ratio varies with different advancing ratios. The maximal liftdrag ratio appeares at the lift-offset of about 20%,25%,30%when μ=0.2,0.4,0.5,respectively.
引文
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[3]BERGQUIST R R,MICHEL P L.Coaxial rigid rotor helicopter and method of flying same:U.S.Patent3409249[P].1968.
[4]PAGLINO V M,BENO E A.Full-scale wind tunnel investigation of the advancing blade concept rotor system[R].SER-50705,1971.
[5]ARTHUR W L,SIMON D.XH-59A ABC? aircraft flight tests at Ft.Rucker,Alabama[J].Aircraft Engineering and Aerospace Technology,1982,54(12):14-18.
[6]FELKER F F.Performance and loads data from a wind tunnel test of a full-scale coaxial hingeless rotor helicopter[R].NASA-A-8732,1981.
[7]LORBER P F,LAW G K,O’NEILL J J.Overview of S-97 RaiderTM scale model tests[C]//The AHS72nd Annual Forum.West Palm Beach,FL,USA:AHS,2016.
[8]BAGAI A.Aerodynamic design of the X2TMtechnology demonstrator main rotor blade[C]//The64th Annual Forum of the American Helicopter Society.Montreal,Canada:AHS,2008.
[9]FEIL R,RAULEDER J,HAJEK M,et al.Computational and experimental aeromechanics analysis of a coaxial rotor system in hover and forward flight[C]//The 42nd European Rotorcraft Forum.Lille,France:European Rotorcraft Society,2016.
[10]邓景辉.高速直升机前行桨叶概念旋翼技术[J].航空科学技术,2012,19(3):9-14.DENG Jinghui.The ABC rotor technology for high speed helicopter[J].Aeronautical Science and Technology,2012,19(3):9-14.
[11]张银.复合式工作刚性旋翼直升机气动干扰及飞行特性分析[D].南京:南京航空航天大学,2014.ZHANG Yin.Research on aerodynamic interaction and flight characteristics of compound helicopter with rigid coaxial rotor[D].Nanjing:Nanjing University of Aeronautics&Astronautics,2014.
[12]江露生,林永峰,樊枫.共轴刚性旋翼悬停气动干扰特性试验研究[C]//第32届中国直升机年会学术论文.绵阳:中国航空协会直升机分会,2016.JIANG Lusheng,LIN Yongfeng,FAN Feng.Experimental investigation of aerodynamic interaction characteristics of rigid coaxial rotors in hover[C]//The 32nd Annual Forum of the China Helicopter Society.Mianyang:The Helicopter Branch of Chinese Society of Aeronautics and Astronautics,2016.
[13]袁明川,刘平安,樊枫.共轴刚性旋翼前飞气动性能风洞试验研究[C]//第32届中国直升机年会学术论文.绵阳:中国航空协会直升机分会,2016.YUAN Mingchuan,LIU Ping’an,FAN Feng.WindTunne-l investigation of the rigid coaxial rotor performance in flight condition[C]//The 32nd Annual Forum of the China Helicopter Society.Mianyang:The Helicopter Branch of Chinese Society of Aeronautics and Astronautics,2016.
[14]黄水林,招启军,徐国华.纵列式双旋翼悬停状态气动干扰特性参数影响分析[J].空气动力学学报,2011,29(2):155-162.HUANG Shuilin,ZHAO Qijun,XU Guohua.Parametric effect investigations on aerodynamic interaction characteristics for tandem rotors in hover[J].Acta Aerodynamica Sinica,2011,29(2):155-162.
[15]BIGGERS J C,CLOUD M C,STROUB R H.An investigation of full-scale helicopter rotors at high advance ratios and advancing tip mach numbers[R].N-ASA TN D-4632,1968.