基于LES方法的气动弹片对风力机翼型气动特性影响研究
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摘要
为分析弹片对翼型气动及噪声方面的影响,以NACA0022为原始翼型,通过在其吸力面加装不同形式的固定气动弹片,比较原始翼型与弹片翼型的气动性能和噪声特性。采用大涡模拟,计算来流风速为29.4 m/s,迎角范围在4°～24°内翼型气动性能和流场分布的变化。研究翼型噪声产生机理,运用FW-H方程进行声学计算,并通过傅里叶转换进行频谱分析。数值计算结果表明:大于12°攻角下,弹片翼型较原始翼型气动性能改善明显,升力系数最大可提高27.31%,且有效推迟翼型的失速产生,单个气动弹片翼型表现更优;大于8°攻角时,气动弹片对监测点处噪声总声压级增大效果并不明显,最大仅为1.90%,且翼型噪声总声压级在指向性分布上呈现较为明显的偶极子分布。
In order to analyze the influence of the shrapnel on the aerodynamic performance and noise characteristics of the airfoil,firstly,the original airfoil of the NACA0022 with different fixed shrapnel on the suction surface is studied by using the LES model in the commercial fluid software FLUENT.The numerical simulation of single and double aerodynamic shrapnel with 0.1 times chord length is carried out.The aerodynamic performance and flow field distribution of the airfoil in the range of 4°～24° are calculated under the wind speed of 29.4 m/s.Then the mechanism of the noise production is studied by using the FW-H equation for the acoustic calculation of the above three airfoil equations and the spectrum analysis by Fourier transform.The results show that the aerodynamic performance of the shrapnel is better than that of the original airfoil under the angle of attack of more than 12°.The lift coefficient can be increased by up to 27.31%,and the stall of the airfoil is effectively delayed,and the single aerodynamic shrapnel airfoil performs better.With the angle of attack greater than 8°,installing shrapnel does not evidently increase the noise amplitude,with the maximum increase of 1.90%,,while the total sound pressure level of airfoil noise has clear directivity,compared to the original airfoil.
In order to analyze the influence of the shrapnel on the aerodynamic performance and noise characteristics of the airfoil,firstly,the original airfoil of the NACA0022 with different fixed shrapnel on the suction surface is studied by using the LES model in the commercial fluid software FLUENT.The numerical simulation of single and double aerodynamic shrapnel with 0.1 times chord length is carried out.The aerodynamic performance and flow field distribution of the airfoil in the range of 4°～24° are calculated under the wind speed of 29.4 m/s.Then the mechanism of the noise production is studied by using the FW-H equation for the acoustic calculation of the above three airfoil equations and the spectrum analysis by Fourier transform.The results show that the aerodynamic performance of the shrapnel is better than that of the original airfoil under the angle of attack of more than 12°.The lift coefficient can be increased by up to 27.31%,and the stall of the airfoil is effectively delayed,and the single aerodynamic shrapnel airfoil performs better.With the angle of attack greater than 8°,installing shrapnel does not evidently increase the noise amplitude,with the maximum increase of 1.90%,,while the total sound pressure level of airfoil noise has clear directivity,compared to the original airfoil.
引文
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[2] SIOZOS-ROUSOULISL,LACOR C,GHORBANIASL G.A flow control technique for noise reduction of a rod-airfoil configuration[J].Journal of Fluids & Structures,2017(69):293-307.
[3] 周云龙,张红芬.襟翼结构对风力机翼型性能的影响及优化设计[J].热能动力工程,2017(1):101-106.ZHOU Yun-long,ZHANG Hong-fen.Effects of flap structure on airfoil performance and optimal design [J] Journal of Engineering for Thermal Energy and Power,2017(1):101-106.
[4] G??MENT,?ZERDEM B.Airfoil optimization for noise emission problem and aerodynamic performance criterion on small scale wind turbines[J].Energy,2012,46(1):62-71.
[5] PAGANIC C,SOUZA D S,MEDEIROS M A F.Experimental investigation on the effect of slat geometrical configurations on aerodynamic noise[J].Journal of Sound & Vibration,2017,394:256-279.
[6] 卓文涛,季锃钏,陈二云,等.翼型气动性能与噪声的综合优化设计方法[J].动力工程学报,2012,32(6):481-486.ZHUO Wen-tao,JI zeng-chuan,Chen er-yun,et al.Aerodynamic performance and noise of airfoil comprehensive optimization design method [J].Journal of Chinese Society of Power Engineering,2012,32(6):481-486.
[7] 徐浩然,杨华,刘超.尾缘加厚的DU系列翼型气动性能数值分析[J].农业工程学报,2014,30(17):101-108.XU Hao-ran,YANG Hua,LIU Chao.Numerical analysis of aerodynamic performance of DU series airfoils thickened at the trailing edge [J].Transactions of the Chinese Society of Agricultural Engineering,2014,30(17):101-108.
[8] 程江涛,陈进,王旭东.基于噪声的风力机翼型优化设计研究[J].太阳能学报,2012,33(4):558-563.CHENG Jiang-tao,CHEN Jin,WANG Xu-dong.Noise-based wind turbine airfoil optimization design [J].Acta Energiae Solaris Sinica,2012,33(4):558-563.
[9] WANGJ,CONG Q,LIANG N,et al.Bionic design and test of small-sized wind turbine blade based on seagull airfoil[J].Transactions of the Chinese Society of Agricultural Engineering,2015,31(10):72-77.
[10] W.LIEBE.Der auftrieb am tragflugel:entstehung und zusammenbruch[J].Aerokurier,1979,12(1):1520-1523.
[11] 李润杰,祖红亚,李春,等.襟翼翼缝相对宽度对翼型动态气动性能的影响[J].热能动力工程,2016,31(4):38-44.LI Run-jie,ZU Hong-ya,LI Chun,et al.Influence of relative width of flap joint on dynamic aerodynamic performance of airfoil [J].Journal of Engineering for Thermal Energy and Power,2016,31(4):38-44.
[12] 郝文星,叶舟,李春,等.基于柔性尾缘襟翼风力机翼型性能主动控制研究[J].太阳能学报,2017,38(5):1339-1345.HAO Wen-xing,YE Zhou,LI Chun,et al.Research on active control of airfoil performance based on flexible tail flap wind turbine [J].Acta Energiae Solaris Sinica,2017,38(5):1339-1345.
[13] SCHLUTER J U.Lift enhancement at low reynolds numbers using self-activated movable flaps[J].Journal of Aircraft,2010,47(1):348-351.
[14] ARIVOLID,SINGH I.Self-adaptive flaps on low aspect ratio wings at low Reynolds numbers[J].Aerospace Science and Technology,2016(59):78-93.
[15] MEYERR,HAGE W,BECHERT D W,et al.Separation control by self-activated movable flaps[J].AIAA Journal,2015,Vol.45(1):191-199.
[16] GOGRAVE,BRAMESFELD T,MAUGHMER M D.Experimental investigation of self-actuating,upper-surface,high-lift-enhancing effectors[J].Journal of Aircraft,2015,39(1):120-124.
[17] SAGAUTP.BOOK REVIEW:Large eddy simulation for incompressible flows.an introduction[J].Bristol:Measurement Science and Technology,2001(12):1745-1746.
[18] HANZ H,SONG W P,QIAO Z D.Aeroacoustic calculation for helicopter rotor in hover and in forward flight based on FW-H equation[J].Acta Aeronautica et Astronautica Sinica,2003,24(5):400-404.
[19] 祁良奎,柳建华,张良,等.叶片副翼摆角对两段式翼型气动性能的影响[J].热能动力工程,2016,31(9):45-51.QI Liang-kui,LIU Jian-hua,ZHANG Liang,et al.Effect of blade ailerons on aerodynamic performance of two-stage airfoils [J].Journal of Engineering for Thermal Energy and Power,2016,31(9):45-51.
[20] MANWELLJ F,MCGOWAN J G,ROGERS A L.Aerodynamics of wind turbines[M].Wind Energy Explained:Theory,Design and Application,Second Edition.2002.
[21] MORFEYC L,WRIGHT M C M.Extensions of Lighthill's acoustic analogy with application to computational aeroacoustics[J].Proceedings Mathematical Physical & Engineering Sciences,2007(463):2101-2127.
[22] WILLIAMS J E,HALL L H.Aerodynamic sound generation by turbulent flow in the vicinity of a scattering half plane[J].Journal of Fluid Mechanics,1970,40(4):657-670.