平均攻角和振幅对振荡翼型气动特性的影响

推进技术 ›› 2015, Vol. 36 ›› Issue (9): 1288-1294.

平均攻角和振幅对振荡翼型气动特性的影响

李绍斌,董贺峰,宋西镇

北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191

发布日期:2021-08-15
作者简介:李绍斌(1980—)，男，博士，讲师，研究领域为叶轮机械气动力学。
基金资助:
国家自然科学基金项目(51106003)。

Effects of Average Attack Angle and Amplitude on Aerodynamic Performance of an Oscillating Airfoil

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics，School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 采用一种基于[k-ω SST]模型和[γ-θ]转捩模型的雷诺平均N-S方程数值方法，对雷诺数Re=1.35×105下的NACA0012振荡翼型和静态翼型非定常流场和升力特性进行模拟，在缩减频率K=0.1的条件下研究了翼型振荡运动中平均攻角和振幅对平均升力系数的影响，并与静态翼型的升力特性及实验结果进行了对比。结果表明:当平均攻角小于临界攻角时，翼型的振荡运动会降低平均升力系数，当平均攻角大于临界攻角同时最小攻角小于临界攻角时，翼型的振荡可以提高平均升力系数。在平均攻角为12°～17°时，翼型振幅为6°左右时可获得最大平均升力系数，与静态翼型相比，平均升力系数可提高30%～45.7%。当振荡过程中最小攻角对应静态翼型轻失速攻角时，翼型上仰阶段前缘涡的产生和集中涡的稳定附着是平均升力系数大幅度阶跃式提升的原因，静态翼型与振荡翼型的组合可提高升力并拓宽攻角范围。

关键词: 振荡翼型；升力系数；转捩模型；平均攻角；振幅

Abstract: The Reynolds average N-S equation enclosed by [k-ω SST] turbulence model and [γ-θ] transition model is adopted to do the numerical simulation for the unsteady flow field and lift characteristics of oscillating and static NACA0012 airfoils. The effects of average attack angle and amplitude on the average lift coefficient are studied in the case of Re=1.35×105 and K=0.1，which is compared with lift characteristics of static airfoil and experimental values. The results show that the oscillatory motion of airfoil will decrease the average lift coefficient if the average attack angle is less than critical angle. And it will increase the average lift coefficient under the condition of the average attack angle greater than critical angle，while the minimal attack angle less than critical angle. In the range of 12°～17°，the oscillating airfoil with amplitude of 6°can provide a better average lift coefficient compared with the static one，and the improvement value is about 30%～45.7%. When the minimal attack angle located in the light stall range of static airfoil，the average lift coefficient will step up during the process of generation of the leading edge vortex and concentrated vortex adhering on the pitching up airfoil. So the combination of static and oscillating airfoils could provide high lift and extend critical angle.

Key words: Oscillating airfoil；Lift coefficient；Transition model；Average attack angle；Amplitude

李绍斌,董贺峰,宋西镇. 平均攻角和振幅对振荡翼型气动特性的影响[J]. 推进技术, 2015, 36(9): 1288-1294.

LI Shao-bin,DONG He-feng,SONG Xi-zhen. Effects of Average Attack Angle and Amplitude on Aerodynamic Performance of an Oscillating Airfoil[J]. Journal of Propulsion Technology, 2015, 36(9): 1288-1294.

参考文献

[1] Carr L W. Progress in Analysis and Prediction of Dynamic Stall[J]. Journal of Aircraft, 1988, 25(1): 6-17.
[2] 符松, 钱炜祺. 翼型动态失速的数值研究[J]. 空气动力学学报, 2001, 19(4): 427-433.
[3] Koochesfahani M M. Vortical Patterns in the Wake of an Oscillating Airfoil[J]. AIAA Journal, 1989, 27(9): 1200-1205.
[4] Ekaterinaris J A, Sorensen N N, Rasmussen F. Numerical Investigation of Airfoil Dynamic Stall in Simultaneous Harmonic Oscillatory and Translatory Motion[J]. Journal of Solar Energy Engineering, 1998, 120(1): 75-83.
[5] Lee T, Gerontakos P. Investigation of Flow Over an Oscillating Airfoil[J]. Journal of Fluid Mechanics, 2004, 512: 313-341.
[6] Kinsey T, Dumas G. Parametric Study of an Oscillating Airfoil in a Power-Extraction Regime[J]. AIAA Journal,2008, 46(6): 1318-1330.
[7] Yu M L, Hu H, Wang Z J. Experimental and Numerical Investigations on the Asymmetric Wake Vortex Structures Around an Oscillating Airfoil[R]. AIAA 2012-0299.
[8] 钱炜祺. 考虑转捩影响的翼型动态失速数值模拟[J].空气动力学学报, 2008, 26(1): 50-55.
[9] Wang S, Ingham D B, Ma L, et al. Numerical Investigations on Dynamic Stall of Low Reynolds Number Flow Around Oscillating Airfoils[J]. Computers & Fluids,2010, 39(9): 1529-1541.
[10] 白鹏, 崔尔杰, 周伟江, 等. 等速上仰翼型动态失速现象研究[J]. 力学学报, 2004, 36(5): 569-576.
[11] 邓小龙, 解亚军. 弹性振动对翼型气动特性影响的数值模拟[J]. 应用力学学报, 2013, (2).
[12] 张正秋, 邹正平, 刘火星. 振荡翼型非定常流动数值模拟研究[J]. 燃气涡轮试验与研究, 2009, 22(3): 1-8.
[13] Castelli M R, Garbo F, Benini E. Numerical Investigation of Laminar to Turbulent Boundary Layer Transition on a NACA 0012 Airfoil for Vertical-Axis Wind Turbine Applications[J]. Wind Engineering, 2011, 35(6): 661-686.
[14] Menter F R, Langtry R B, Likki S R, et al. A Correlation-Based Transition Model Using Local Variables: Part I—Model Formulation[R].ASME 2004-GT-53452.
[15] Langtry R B, Menter F R, Likki S R, et al. A Correlation-Based Transition Model Using Local Variables—Part II: Test Cases and Industrial Applications[J]. Journal of Turbomachinery, 2004; 128(3): 423-434.
[16] Shengyi Wang, Lin Ma, Derek B Ingham, et al. Turbulence Modelling of Deep Dynamic Stall at Low Reynolds Number[C].London: Proceedings of the World Congress on Engineering, 2010.
[17] 郑赟, 李虹杨, 刘大响. γ-Reθ转捩模型在高超声速下的应用及分析[J]. 推进技术, 2014, 35(3): 296-304. ( ZHENG Yun, LI Hong-yang, LIU Da-xiang.Application and Analysis of γ-Reθ Transition Model in Hypersonic Flow[J]. Journal of Propulsion Technology,2014, 35(3): 296-304.)
[18] 李涛, 边昕, 冯宇, 等. 基于Gama-Theta转捩模型的气冷涡轮气热耦合研究[J]. 推进技术, 2014, 35(7): 932-940. (LI Tao,BIAN Xin,FENG Yu, et al. Conjugate Heat Transfer Simulation of Air-Cooled Turbine Based on Gama-Theta Transition Model[J]. Journal of Propulsion Technology, 2014, 35(7): 932-940.)(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-06-13；修订日期:2014-09-09。基金项目:国家自然科学基金项目(51106003)。作者简介:李绍斌(1980—),男,博士,讲师,研究领域为叶轮机械气动力学。E-mail: lee_shaobin@buaa.edu.cn