基于后缘小翼的旋翼翼型动态失速控制分析

doi:10.7527/S1000-6893.2016.0220

Abstract

Abstract:

Control effects of typical motion parameters of trailing-edge flap (TEF) on the dynamic stall characteristics of rotor airfoil are investigated. A high-efficiency and high-precision CFD method for predicting the unsteady flow characteristics of rotor airfoil with TEF control is developed. The viscous and orthogonal body-fitted grids around the oscillatory rotor airfoil are regenerated by solving Poisson equations. To ensure the quality of the grids around TEF, a reconstruction of grid points on airfoil is conducted to describe the motion of TEF. Aiming at overcoming the shortcoming of deformable grid approach, which may result in the distortion of grid, a moving-embedded grid method is developed to predict the flowfield of the oscillatory airfoil with TEF control. Based on unsteady Reynolds averaged Navier-Stokes (URANS) equations, dual-time method, Spalart-Allmaras (S-A) turbulence model, and Roe-Monotone Upwind-centered Scheme for Conservation Laws (Roe-MUSCL) scheme, a high-precision CFD method for predicting the flowfield around airfoil is developed, and implicit Lower-Upper Symmetric Gauss-Seidel (LU-SGS) scheme and parallel techniques are adopted to improve computational efficiency. The dynamic stall cases of HH-02 and SC1095 rotor airfoils are calculated using the proposed method. It is demonstrated that the hysteresis effects are well captured, verifying the effectiveness of numerical simulation method. Focusing on the dynamic stall cases of SC1095 rotor airfoil, analyses on dynamic stall control via TEF are carried out. The function P_o and P_c which can reflect the lift, drag and moment characteristics of airfoil are proposed. The effects of the non-dimensional frequency, the phase difference and the angular amplitude of the trailing-edge flap are revealed. The results indicate that dynamic stall phenomenon of an oscillatory airfoil could be significantly suppressed when relative motion frequency of the trailing-edge flap is 1.0 and the phase difference is about 0°. At this state, the maximum drag and negative moment coefficients of SC1095 airfoil can be reduced by about 19% and 27% respectively via TEF control when the angular amplitude is 10°.

Key words: rotor, airfoil, dynamic stall, trailing-edge flap, parametric analysis, unsteady Reynolds averaged Navier-Stokes equation

CLC Number:

MA Yiyang, ZHAO Qijun, ZHAO Guoqing. Dynamic stall control of rotor airfoil via trailing-edge flap[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(3): 120312-120312.

References

[1] CONLISK A T. Modern helicopter rotor aerodynamics[J]. Progress in Aerospace Sciences, 2002, 37(5):417-476.
[2] VIEIRA B A O, MAUGHMER M D. An evaluation of dynamic stall onset prediction methods for rotorcraft airfoil design:AIAA-2013-1093[R]. Reston:AIAA, 2013.
[3] GEISSLER W, RAFFEL M, DIETZ G, et al. Helicopter aerodynamics with emphasis placed on dynamic stall[M]. Heidelberg:Springer, 2007:199-204.
[4] CHOPRA I. Review of state of art of smart structures and integrated systems[J]. AIAA Journal, 2002, 40(11):2145-2187.
[5] CARR L. The effect of a leading-edge slat on the dynamic stall of an oscillating airfoil:AIAA-1983-2533[R]. Reston:AIAA, 1983.
[6] POST M L, CORKE T C. Separation control using plasma actuators:Dynamic stall vortex control on oscillating airfoil[J]. AIAA Journal, 2006, 44(12):3125-3135.
[7] ZHAO G Q, ZHAO Q J. Dynamic stall control optimization of rotor airfoil via variable droop leading-edge[J]. Aerospace Science & Technology, 2015, 43(6):406-414.
[8] JAWORSKI J W. Thrust and aerodynamic forces from an oscillating leading-edge flap[J]. AIAA Journal, 2012, 50(12):2928-2931.
[9] PECHAN T. Design and analysis of an active leading edge wing:AIAA-2013-01222[R]. Reston:AIAA, 2013.
[10] CHANDRASEKHARA M S. A review of compressible dynamic stall control principles and methods[C]//Proceedings of the Tenth Asian Congress of Fluid Mechanics. ACFM, 2004:1-6.
[11] FESZTY D, GILLIES E A, VEZZA M. Alleviation of airfoil dynamic stall moments via trailing-edge flap flow control[J]. AIAA Journal, 2004, 42(1):17-25.
[12] KRZYSIAK A, NARKIEWICZ J. Aerodynamic loads on airfoil with trailing-edge flap pitching with different frequencies[J]. Journal of Aircraft, 2006, 43(2):407-418.
[13] GERONTAKOS P, LEE T. Trailing-edge flap control of dynamic pitching moment[J]. AIAA Journal, 2012, 45(7):1688-1694.
[14] LEE T, SU Y Y. Unsteady airfoil with a harmonically deflected trailing-edge flap[J]. Journal of Fluids & Structures, 2011, 27(8):1411-1424.
[15] 王进, 杨茂, 陈凤明. 带后缘襟翼翼型的非定常气动特性数值仿真[J]. 计算机仿真, 2011, 28(2):88-92. WANG J, YANG M, CHEN F M. CFD simulation of unsteady aerodynamic of airfoil with trailing-edge flap[J]. Computer Simulation, 2011, 28(2):88-92(in Chinese).
[16] 刘洋, 向锦武. 后缘襟翼对直升机旋翼翼型动态失速特性的影响[J]. 航空学报, 2013, 34(5):1028-1035. LIU Y, XIANG J W. Effect of the trailing edge flap on dynamic stall performance of helicopter rotor airfoil[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(5):1028-1035(in Chinese).
[17] 王荣, 夏品奇. 多片后缘小翼对直升机旋翼桨叶动态失速及桨毂振动载荷的控制[J]. 航空学报, 2013, 34(5):1083-1091. WANG R, XIA P Q. Control of helicopter rotor blade dynamic stall and hub vibration loads by using multiple trailing edge flaps[J]. Acta Aeronautica et Astronautica Sinica, 2013,34(5):1083-1091(in Chinese).
[18] 王博, 招启军, 徐广, 等. 一种适合于旋翼前飞非定常流场计算的新型运动嵌套网格方法[J]. 空气动力学学报, 2012, 30(1):14-21. WANG B, ZHAO Q J, XU G, et al. A new moving-embedded grid method for numerical simulation of unsteady flow-field of the helicopter rotor in forward flight[J]. Acta Aerodynamica Sinica, 2012, 30(1):14-21(in Chinese).
[19] 赵国庆, 招启军, 王清. 旋翼翼型非定常动态失速特性的CFD模拟及参数分析[J]. 空气动力学学报, 2015, 33(1):72-81. ZHAO G Q, ZHAO Q J, WANG Q. Simulations and parametric analyses on unsteady dynamic stall characteristics of rotor airfoil based on CFD method[J]. Acta Aerodynamica Sinica, 2015, 33(1):72-81(in Chinese).
[20] MCALISTER K W, PUCCI S L, MCCROSKEY W J, et al. An experimental study of dynamic stall on advanced airfoil section. Volume 2:Pressure and force data:NASA TM-84245[R]. Washington, D.C.:NASA, 1982.

Dynamic stall control of rotor airfoil via trailing-edge flap

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