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
    
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
Download:   PDF(2652KB) HTML
Export: BibTeX | EndNote (RIS)      

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．

Published: 01 January 2014
CLC:  V 211.3  
Service
E-mail this article
Add to my bookshelf
Add to citation manager
E-mail Alert
RSS
Articles by authors
Cite this article:

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

URL:

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


耦合运动的襟翼-翼型气动特性数值仿真

 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.

［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] LIU Feng, ZOU Jian-feng, ZHENG Yao. Effect of synthetic jets physical parameters on
flow separation control over airfoil[J]. J4, 2013, 47(1): 146-153.