Effect of blade camber on aerodynamic performance of cycloidal propeller under hovering status
-
摘要: 以悬停状态下的摆线桨为研究对象,利用数值模拟方法,分别研究了桨叶相对弯度X和最大弯度位置Y对摆线桨气动性能的影响。结果表明:与桨叶为对称翼型的摆线桨相比,当桨叶具有一定弯度且最大弯度位置适中时,摆线桨气动性能得到很大的提升。当桨叶相对弯度X为4%C(C为翼型弦长)、最大弯度位置Y距离前缘40%C~50%C时,摆线桨升力和气动功耗比较低,悬停效率最高,整体气动性能更好。Abstract: A series of cycloidal propellers were studied numerically under hovering status. The effects of the blade relative camber X and the location of the maximum camber Y of the blade on the aerodynamic performance of cycloidal propeller were studied respectively. The results indicated that compared with the cycloidal rotors with the blades of symmetrical airfoils, the aerodynamic performance of cycloidal propeller was improved greatly under the moderate camber and appropriate location of the maximum camber of the blade chord. When the relative camber X was 4%C (C was chord length) and the location of the maximum camber Y was at 40%C-50%C from the leading edge, the lift and power of the cycloidal propeller were relatively lower, the hovering efficiency was higher than other conditions, and the overall aerodynamic performance was better.
-
[1] YUN C Y.A new vertical take-off and landing aircraft with cycloidal blades system:cyclocopter[D].Seoul:Seoul National University,2004. [2] BENEDICT M,RAMASAMY M,CHOPRA I,et al.Performance of a cycloidal rotor concept for micro air vehicle applications[J].Journal of the American Helicopter Society,2010,55(2):22002.1-22002.14. [3] JARUGUMILLI T,BENEDICT M,CHOPRA I.Experimental optimization and performance analysis of a MAV scale cycloidal rotor[R].AIAA-2011-821,2011. [4] 唐继伟,胡峪,宋笔锋.摆线桨气动性能研究进展[J].空气动力学学报,2013,31(5):676-684.TANG Jiwei,HU Yu,SONG Bifeng.Advances in the aerodynamics research of cycloidal propeller[J].Acta Aerodynamica Sinica,2013,31(5):676-684.(in Chinese) [5] 杜帆,胡峪.滚翼机滚转阶跃响应分析[J].飞行力学,2014,32(2):118-121.DU Fan,HU Yu.Analysis of roll step-input response of a cyclogyro[J].Flight Dynamics,2014,32(2):118-121.(in Chinese) [6] HU Yu,LIM K B,HU Wenrong.The research on the performance of cyclogyro[R].AIAA-2006-7704,2006. [7] ANDREWS G,SHRESTHA E,CHOPRA I.Design and fabrication of a meso-scale aircraft using a cycloidal rotor propulsion system[R].AIAA-2016-0141,2016. [8] HWANG I S,MIN S Y,KIM M K,et al.Multidisciplinary optimal design of cyclocopter blade system[R].AIAA-2005-2287,2005. [9] KIM S J,YUN C Y,KIM D,et al.Design and performance tests of cycloidal propulsion systems[R].AIAA-2003-1786,2003. [10] PARSONS E S.Investigation and characterization of a cycloidal rotor for application to a micro-air vehicle[D].Washington DC:University of Maryland,2005. [11] SIROHI J,PARSONS E,CHOPRA I.Hover performance of a cycloidal rotor for a micro air vehicle[J].Journal of the American Helicopter Society,2007,52(3):263-279. [12] LEGER J A,PSCOA J C,XISTO C M.Analytical modeling of a cyclorotor in hovering state[J].Proceedings of the Institution of Mechanical Engineers:Part G Journal of Aerospace Engineering,2015,229(12):2163-2177. [13] IOSILEVSKII G,LEVY Y.Experimental and numerical study of cyclogiro aerodynamics[J].AIAA Journal,2006,44(12):2866-2870. [14] IOSILEVSKII G,LEVY Y.Aerodynamics of the cyclogiro[R].AIAA-2003-3473,2003. [15] BENEDICT M,JARUGUMILLI T,LAKSHMINARAYAN V,et al.Effect of flow curvature on forward flight performance of a micro-air-vehicle-scale cycloidal-rotor[J].AIAA Journal,2014,52(6):1159-1169. [16] BENEDICT M,JARUGUMILLI T,CHOPRA I.Effect of rotor geometry and blade kinematics on cycloidal rotor hover performance[J].Journal of Aircraft,2013,50(5):1340-1352. [17] BENEDICT M,RAMASAMY M,CHOPRA I.Improving the aerodynamic performance of micro-air-vehicle-scale cycloidal rotor:an experimental approach[J].Journal of Aircraft,2010,47(4):1117-1125. [18] SEIFERT J.A review of the Magnus effect in aeronautics[J].Progress in Aerospace Sciences,2012,55(5):17-45. [19] MCNABBM L.Development of a cycloidal propulsion computer model and comparison with experiment[D].Starkville,US:Mississippi State University,2001. [20] JAMESON A.An assessment of dual-time stepping,time spectral and artificial compressibility based numerical algorithms for unsteady flow with applications to flapping wings[R].AIAA-2009-4273,2009. [21] 杨金广,吴虎.双方程κ-ω SST湍流模型的显式耦合求解及其在叶轮机械中的应用[J].航空学报,2014,35(1):116-124.YANG Jinguang,WU Hu.Explicit coupled solution of two-equation κ-ω SST turbulence model and its application in turbomachinery flow simulation[J].Acta Aeronautica et Astronautica Sinica,2014,35(1):116-124.(in Chinese)
点击查看大图
计量
- 文章访问数: 563
- HTML浏览量: 2
- PDF量: 448
- 被引次数: 0