Please wait a minute...
浙江大学学报(工学版)
J4  2014, Vol. 48 Issue (1): 149-153    DOI: 10.3785/j.issn.1008-973X.2014.01.023
航空航天技术     
耦合运动的襟翼-翼型气动特性数值仿真
杨茂,徐珊珊
西北工业大学 航天学院,陕西 西安 710072
Numerical simulation of aerodynamics of coupled flapping-pitching airfoil with trailing-edge flap
YANG Mao,XU Shan-shan
School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
 全文: PDF(2652 KB)   HTML
摘要：

 为了研究采用主动后缘襟翼的智能旋翼在高速前飞状态下,耦合运动对襟翼-翼型的气动特性和动态失速特性的影响,通过数值求解Navier-Stokes方程来模拟作挥舞-变距耦合运动的襟翼-翼型的气动特性.湍流模型为雷诺平均的Spalart-Allmaras模型.结果显示,与单纯变距运动相比,当与变距运动同频、同相的挥舞运动耦合后,耦合运动会引起更大的气动系数超调和滞回环；耦合运动会增大黏性干扰区域尺度,使襟翼-翼型失速类型由动态轻失速变为动态深失速；耦合运动会增大力矩系数对流场变化的敏感度.
Abstract:

Navier-Stokes equations were numerically solved with Reynolds averaged Spalart-Allmaras turbulence model in order to analyze the effects of coupled flapping-pitching oscillation on the unsteady aerodynamics and dynamic stall characteristics of an airfoil with active trailing-edge flap (TEF) at high speed forward flight. Results show that compared to simple pitching airfoil with TEF, when flapping oscillating with same frequency and phase is added, higher overshoot of aerodynamic coefficients and larger hysteresis loops are observed. Coupled oscillation increases area of viscous interaction resulting in deep dynamic stall instead of light dynamic stall. Coupled oscillation increases the sensitivity of pitching moment coefficient on flow-field variation．
出版日期: 2014-01-01
:  V 211.3  
基金资助:

国家自然科学基金资助项目（10872170）.
作者简介: 杨茂（1973-），男，副教授，从事旋翼动力学的研究.E-mail：yang_mao@nwpu.edu.cn
服务　　
把本文推荐给朋友
加入引用管理器
E-mail Alert
RSS
作者相关文章　　

引用本文:

杨茂,徐珊珊. 耦合运动的襟翼-翼型气动特性数值仿真[J]. J4, 2014, 48(1): 149-153.

YANG Mao,XU Shan-shan. Numerical simulation of aerodynamics of coupled flapping-pitching airfoil with trailing-edge flap. J4, 2014, 48(1): 149-153.

链接本文:

http://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2014.01.023    或    http://www.zjujournals.com/eng/CN/Y2014/V48/I1/149

［1］ BARRETT R, SCHLIESMAN M, FRYE P. Design development and testing of a mini solid state adaptive rotorcraft ［C］∥ Proceedings of 1997 Symposium on Smart Materials, Structures and MEMs. San Diego: SPIE, 3041: 231-242．
［2］ FRIEDMANN P, MILLOTT T. Vibration reduction in rotorcraft using active control: a comparison of various approaches ［J］. Journal of Guidance, Control and Dynamics, 1995, 18(4): 664-673．
［3］ DIETERICH O, ENENKL B, ROTH D. Trailing edge flaps for active rotor control aeroelastic characteristics of the ADASYS rotor system ［C］∥Proceedings of the 62nd American Helicopter Society Annual Forum. Phoenix: AHS, 2006．
［4］ THEODORSEN T, GARRICK I E. Nonstationary flow about a wing-aileron-tab combination, including aerodynamic balance ［R］. ［S. l.］: NACA, 1943．
［5］ HARIHARAN N, LEISHMAN J G. Unsteady aerodynamics of a flapped airfoil in subsonic flow by indicial concepts ［J］. Journal of Aircraft, 1995, 33(5): 855-868．
［6］ CARTA F O. A comparison of the pitching and plunging response of an oscillating airfoil ［R］. ［S. l.］: NASA, 1979．
［7］ KRZYSIAK A, NARKIEWICZ J. Aerodynamic loads on airfoil with trailing-edge flap pitching with different frequencies ［J］. Journal of Aircraft, 2006, 43(2): 407418．
［8］ GERONTAKOS P, LEE T. Trailing-edge flap control of dynamic pitching moment ［J］. AIAA Journal, 2007, 45(7): 16881694．
［9］ GILLIES E A, GREEN R B, WANG Y, et al. Trailing edge flap flow control for dynamic stall ［C］∥ Proceedings of the American Helicopter Society Aeromechanics Specialists Conference. San Francisco: AHSI, 2010: 1-14．
［10］ FESZTY D, GILLIES E A, VEZZA M. Alleviation of rotor blade dynamic stall moments via trailing edge flap flow control ［C］∥ Proceedings of 41st Aerospace Sciences Meeting and Exhibit. Nevada: AIAA, 2003-50: 1-10．
［11］ LIU L, FRIEDMANN P P, PADTHE A K. Comparison of approximate time domain aerodynamics for flapped airfoils with CFD based results with applications CFD and lower order models ［C］∥Proceedings of the AHS Specialists Conference. San Francisco: AHSI, 2008: 940-956．
［12］ JOSE A I, BAEDER J D. Steady and unsteady aerodynamic modeling of trailing edge flaps with overhang and gap using CFD and lower order models ［C］∥ Proceedings of 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition. Florida: AIAA, 2009-1071:1-19．
［13］ MCCROSKEY M J. The phenomenon of dynamic stall ［R］. ［S. l.］: NASA, 1981．
[1] 刘峰, 邹建锋, 郑耀. 合成射流物理参数对控制翼型流动分离的影响[J]. J4, 2013, 47(1): 146-153.