ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Experimental Research and Numerical Analysis on Aerodynamic Characteristics of Rotors with Improved CLOR Blade-tip
Received date: 2012-02-29
Revised date: 2012-07-09
Online published: 2012-08-01
Supported by
National Natural Science Foundation of China (10872094)
Wind tunnel test and numerical simulation are performed to investigate the aerodynamic characteristics of rotors with an improved CLOR (CLOR-Ⅱ)blade-tip in hover and forward flight. Taking into consideration the unsteady characteristics of the rotor flowfield, and aiming at advanced aerodynamic performance of the rotors in both hover and forward flight, the aerodynamic shape of the rotor blade is redesigned using aerodynamic analysis based on the investigations of rotors with CLOR tip. It mainly includes the optimal allocation of airfoils on the spanwise direction of the rotor blade for improving such properties as advancing blade compressibility and retreating blade dynamic stall, and the shape of the blade tip is designed meticulously taking into account the dynamic characteristics of the blade in forward flight. The three types of rotors are measured in a wind tunnel under multi-conditions. Based on these, the aerodynamic characteristics of rotors under the same conditions with the tests are simulated by computational fluid dynamics (CFD) and the calculated results are compared with the experimental results. Additionally, higher speed rotation conditions are also computed. Results show that the obvious advantages of the rotors with CLOR-Ⅱ tip in suppressing the transonic strength and increasing the stall angle of attack are demonstrated by comparing with the other two types of rotors, and the characteristics of the rotors in hover and forward flight are comprehensive improved.
WANG Bo , ZHAO Qijun , ZHAO Guoqing , XU Guohua . Experimental Research and Numerical Analysis on Aerodynamic Characteristics of Rotors with Improved CLOR Blade-tip[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(2) : 235 -245 . DOI: 10.7527/S1000-6893.2013.0027
[1] Leishman J G. Principles of helicopter aerodynamics. Cambridge: Cambridge University Press, 2006.
[2] Wilby P G. The development of rotor airfoil testing in the UK. Journal of the American Helicopter Society, 2001, 46(3): 210-220.
[3] Yeager W T, Jr, Noonan K W, Singleton J D, et al. Performance and vibratory loads data from a wind-tunnel test of a model helicopter main-rotor blade with a paddle-type tip. NASA-ADA-406400, 1997.
[4] Toulmay F V, Falchero D A. Blade for aircraft rotary wings, with swept-back tip: US. 6000911. 1994-07-26.
[5] Desopper A, Lafon P, Philippe J J, et al. Effect of an anhedral sweptback tip on the performance of a helicopter rotor. VERTICA, 1988, 12(4): 345-355.
[6] Philippe J J, Chattot J J. Experimental and theoretical studies on helicopter blade tips at ONERA. ONERA-1980-96, 1980.
[7] Harrison R, Stacey S, Hansford B. BERP IV-the design, development and testing of an advanced rotor blade. Proceedings of American Helicopter Society Annual Forum, 2008, 64(2): 1334.
[8] Prieur J, Lafon P, Caplot M, et al. Aerodynamics and acoustics of rectangular and swept rotor blade tips. Journal of the American Helicopter Society, 1989, 34(1): 42-51.
[9] Bagai A, Leishman J G. Rotor free-wake modeling using a pseudo-implicit technique—including comparisons with experimental data. Journal of the American Helicopter Society, 1995, 40(3): 29-41.
[10] Rocchetto A, Poloni C. A hybrid numerical optimization technique based on genetic and feasible direction algorithms for multipoint helicopter rotor blade design. 21st European Rotorcraft Forum, 1995.
[11] Bennett R L. Application of optimization methods to rotor design problems. Vertica, 1983, 7(3): 201-208.
[12] Xu G H. Investigation on aerodynamic characteristics of helicopter rotor with new blade tip by the free wake analysis. Nanjing: Nanjing University of Aeronautics and Astronautics, 1996. (in Chinese) 徐国华. 应用自由尾迹分析的新型桨尖旋翼气动特性研究. 南京: 南京航空航天大学, 1996.
[13] Ganguli R. Survey of recent developments in rotorcraft design optimization. Journal of Aircraft, 2004, 41(3): 493-510.
[14] Leoni R D. Black hawk: the story of a world class helicopter. New York: American Institute of Aeronautics and Astronautics, 2007.
[15] Song W P, Han Z H, Wang L Q, et al. The effect of blade-tip shape on rotor aeroacoustic noise by Euler/Kirchhoff method. Chinese Journal of Computation Physics, 2001, 18(6): 569-572. (in Chinese) 宋文萍, 韩忠华, 王立群, 等. 旋翼桨尖几何形状对旋翼气动噪声影响的定量计算分析. 计算物理, 2001, 18(6): 569-572.
[16] Lin Y F, Liu P A, Chen W X, et al. Measurement of blade pressure distribution for three-dimensional blade tip. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(3): 346-350. (in Chinese) 林永峰, 刘平安, 陈文轩, 等. 三维桨尖旋翼桨叶表面压力测量试验. 南京航空航天大学学报, 2011, 43(3): 346-350.
[17] Yang W D, Deng J H. Aeroelastic stability analysis of helicopter rotor blade with swept tips. Journal of Nanjing University of Aeronautics & Astronautics, 2003, 35(3): 248-252. (in Chinese) 杨卫东, 邓景辉. 直升机后掠桨尖旋翼气弹稳定性研究. 南京航空航天大学学报, 2003, 35(3): 248-252.
[18] Zhao Q J, Xu G H. Aeroelastic stability analysis of helicopter rotor blade with swept tips. Acta Aeronautica et Astronautica Sinica, 2009, 30(3): 422-429. (in Chinese) 招启军, 徐国华. 新型桨尖旋翼悬停气动性能试验及数值研究. 航空学报. 2009, 30(3): 422-429.
[19] Harten A, Hyman J M. Self adjusting grid methods for one-dimensional hyperbolic conservation laws. Journal of Computational Physics, 1983, 50(2): 235-269.
[20] Spalart P R, Allmaras S R. A one-equation turbulence model for aerodynamic flows. AIAA-1992-0439, 1992.
[21] Lorber P F, Stauter R C, Landgrebe A J. A comprehensive hover test of the airloads and airflow of an extensively instrumented model helicopter rotor. 45th Annual Forum of American Helicopter Society, 1989: 281-295.
/
〈 |
|
〉 |