NACA0012翼型前缘气动噪声控制实验研究
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- 英文论文题名：An Experimental Study on Leading-edge Noise Control over a NACA0012 Airfoil
- 论文作者：王勇 ; 陈鹏 ; 郑谢 ; 唐道锋 ; 卢翔宇
- 英文论文作者：Wang Yong ; Chen Peng ; Zheng Xie ; Tang dao-feng ; Lu Xiang-yu ; State Key Laboratory of Aerodynamics ; China Aerodynamics Research and Development Center ; Key Laboratory of Aerodynamic Noise Control ; China Aerodynamics Research and Development Center
- 年：2016
- 作者机构：中国空气动力研究与发展中心空气动力学国家重点实验室;中国空气动力研究与发展中心气动噪声控制重点实验室;
- 论文关键词：气动噪声 ; 仿生学 ; 翼型 ; 前缘噪声 ; 蒙皮 ; 穿孔板 ; 空腔
- 英文论文关键词：aerodynamic noise ; boinics ; airfoil ; leading-edge noise ; skin ; perforated plate ; cavity
- 会议召开时间：2016-11-04
- 会议录名称：2016年度全国气动声学学术会议论文摘要集
- 语种：中文
- 分类号：V211.41
- 学会代码：LTLX
- 会议名称：2016年度全国气动声学学术会议
- 会议地点：中国北京
- 主办单位：中国航空学会航空声学专业委员会、中国航空学会气动声学专业委员会、中国商飞上海飞机设计研究院、北京航空航天大学
- 学会名称：北京航空航天大学流体力学教育部重点实验室
- 页数：7
- 文件大小：507k
- 原文格式：D
- 会议级别：全国
摘要
当机翼位于强湍流流场中时,前缘噪声是机翼气动噪声的主要噪声源。对机翼前缘气动噪声的控制研究,除了采用先进的能产生更低噪声的翼型设计外,基于仿生学的机翼前缘气动噪声控制方法是近年来的研究热点。受静音飞行鸮翅膀表面和躯体部位降噪特征的启发,本文建立了一种新颖的前缘仿生改形模型:表面弹性蒙皮+穿孔板+空腔。以NACA0012翼型为研究对象,通过声学风洞实验初步测量了前缘仿生改形前后的噪声水平。实验结果表明,本文提出的前缘仿生改形方法能有效地抑制湍流与翼型前缘相互作用而产生的噪声,能使总声压级降低约20dB。
Leading edge noise is a major noise source when an airfoil is subject to a turbulent flow.Besides the possibility to choose advenced airfoil designs that are known to generate less noise than others, the reduction of airfoil leading edge noise by means of bionics is a research hotspots during the last decade.Inspired by the silent flight characteristics of the wing surface and body of the owl, we proposed a new-style structure for the modification of the leading edge where the airfoil is composed of elastic skin, perforated plate and cavity.Preliminary aeroacoustic measurements have been carried out in the anechoic wind tunnel by a NACA-0012 airfoil with both the standardized and modified leading edges.It is found that the proposed method can effectively suppress the noise generated by the interaction of the turbulence and the leading edge of the airfoil, and the noise reduction of the overall sound pressure level can reach up to 20 dB.
Leading edge noise is a major noise source when an airfoil is subject to a turbulent flow.Besides the possibility to choose advenced airfoil designs that are known to generate less noise than others, the reduction of airfoil leading edge noise by means of bionics is a research hotspots during the last decade.Inspired by the silent flight characteristics of the wing surface and body of the owl, we proposed a new-style structure for the modification of the leading edge where the airfoil is composed of elastic skin, perforated plate and cavity.Preliminary aeroacoustic measurements have been carried out in the anechoic wind tunnel by a NACA-0012 airfoil with both the standardized and modified leading edges.It is found that the proposed method can effectively suppress the noise generated by the interaction of the turbulence and the leading edge of the airfoil, and the noise reduction of the overall sound pressure level can reach up to 20 dB.
引文
[1]Geyer T,Sarradj E,Giesler J,et al.Experimental assessment of the noise generated at the leading edge of porous airfoils using microphone array techniques,AIAA 2011-2713[R].Reston:AIAA,2011.
[2]Sharland I J.Sources of noise in axial flow fans[J].Journal of Sound and Vibration,1964,3:302-322.
[3]Wagner S,Bareiss R,Guidati G.Wind turbine noise[M].Springer,1996.
[4]Lu Y X.Significance and progress of bionics[J].J Bionic Eng,2004,1(1):1-3.
[5]Roger E A,Robert T N.Effect of leading edge serrations on noise radiation from a model rotor,AIAA 72-655[R].Reston:AIAA,1972.
[6]Narayanan S,Chaitanya P,Haeri S,et al.Aifoil noise reductions through leading edge serrations[J].Physics of Fluids,2015,27,025109.
[7]Ren L Q,Sun S M,Xu C Y.Noise reduction mechanism of non-smooth leading edge of owl wing[J],Journal of Jilin University(Engineering and Technology Edition),2008,38:126-131(in Chinese).任露泉,孙少明,徐成宇.鸮翼前缘非光滑形态消声降噪机理[J].吉林大学学报(工学版),2008,38:126-131.
[8]Xu C Y,Qian Z H,Liu Q P,et al.Aerodynamic performance of bionic coupled foils based on leading edge of long-eared owl wing[J],Journal of Jilin University(Engineering and Technology Edition),2010,40(1):108-?112(in Chinese).徐成宇,钱志辉,刘庆萍等.基于长耳鸮翼前缘的仿生耦合翼型气动性能[J].吉林大学学报(工学版),2010,40(1):108-112.
[9]Liu X M,Li S.Effects of bionic volute tongue bioinspired by leading edge of owl wing on aerodynamic performance and noise of multi-blade centrifugal fan[J].Journal of Xi’an Jiaotong University,2015,49(1):14-20(in Chinese).刘小民,李烁.仿鸮翼前缘蜗舌对多翼离心风机气动性能和噪声的影响[J].西安交通大学学报,2015,49(1):14-20.
[10]Soderman P T.Leading-edge serrations which reduce the noise of low-speed rotors,NASA TN D-7371[R].1973.
[11]Hersh A S,Hayden R E.Aerodynamic sound radiation from lifting surfaces with and without leading-edge serrations,NASACR-114370[R].1971.
[12]Hersh A S,Soderman P T,Hayden R E.Investigation of acoustic effects of leading-edge serrations on airfoils[J].Journal of Aircraft,1974,11(4):197-202.
[13]Lee S.Reduction of blade-vortex interaction noise through porous leading edge[J].AIAA Journal,1994,32(3):480-488.
[14]Tinetti A F,Kelly J F,Thomas R H,et al.Reduction of wake-stator interaction noise using passive porosity,AIAA 2002-1036[R].Reston:AIAA,2012.
[15]Graham R R.The silent flight of owls[J].The Journal of the Royal Aeronautical Society,1934,38:837-843.
[16]Sun S M,Ren L Q,Xu C Y.Research on coupling sound absorption property of owl skin and feather[J].Noise and Vibration Control,2008,3:119-123(in Chinese).孙少明,任露泉,徐成宇.长耳鸮皮肤和覆羽耦合吸声降噪特性研究[J].噪声与振动控制,2008,3:119-123.
[17]Jacob M C,Boudet J,Casalino D,et al.A rod-airfoil experiment as benchmark for broadband noise modeling[J].Theoretical and Computational Fluid Dynamics,2005,19:171-196.
[18]Casalino D,Jacob M,Roger M.Prediction of rod-airfoil interaction noise using the Ffowcs-Williams-Hawkings analogy[J].AIAA,Journal,2003,41(2):182-191.
[19]Lorenzoni V,Moore P,Scarano F,et al.Aeroacoustic analysis of a rod-airfoil Flow by means of timeresolved PIV,AIAA 2009-3298[R].Reston:AIAA,2009.
[20]Moore P,Lorenzoni V,Scarano F.Two techniques for PIV-based aeroacoustic prediction and their application to a rod-airfoil experiment[J].Exp Fluids(2011)50:877-885.
[2]Sharland I J.Sources of noise in axial flow fans[J].Journal of Sound and Vibration,1964,3:302-322.
[3]Wagner S,Bareiss R,Guidati G.Wind turbine noise[M].Springer,1996.
[4]Lu Y X.Significance and progress of bionics[J].J Bionic Eng,2004,1(1):1-3.
[5]Roger E A,Robert T N.Effect of leading edge serrations on noise radiation from a model rotor,AIAA 72-655[R].Reston:AIAA,1972.
[6]Narayanan S,Chaitanya P,Haeri S,et al.Aifoil noise reductions through leading edge serrations[J].Physics of Fluids,2015,27,025109.
[7]Ren L Q,Sun S M,Xu C Y.Noise reduction mechanism of non-smooth leading edge of owl wing[J],Journal of Jilin University(Engineering and Technology Edition),2008,38:126-131(in Chinese).任露泉,孙少明,徐成宇.鸮翼前缘非光滑形态消声降噪机理[J].吉林大学学报(工学版),2008,38:126-131.
[8]Xu C Y,Qian Z H,Liu Q P,et al.Aerodynamic performance of bionic coupled foils based on leading edge of long-eared owl wing[J],Journal of Jilin University(Engineering and Technology Edition),2010,40(1):108-?112(in Chinese).徐成宇,钱志辉,刘庆萍等.基于长耳鸮翼前缘的仿生耦合翼型气动性能[J].吉林大学学报(工学版),2010,40(1):108-112.
[9]Liu X M,Li S.Effects of bionic volute tongue bioinspired by leading edge of owl wing on aerodynamic performance and noise of multi-blade centrifugal fan[J].Journal of Xi’an Jiaotong University,2015,49(1):14-20(in Chinese).刘小民,李烁.仿鸮翼前缘蜗舌对多翼离心风机气动性能和噪声的影响[J].西安交通大学学报,2015,49(1):14-20.
[10]Soderman P T.Leading-edge serrations which reduce the noise of low-speed rotors,NASA TN D-7371[R].1973.
[11]Hersh A S,Hayden R E.Aerodynamic sound radiation from lifting surfaces with and without leading-edge serrations,NASACR-114370[R].1971.
[12]Hersh A S,Soderman P T,Hayden R E.Investigation of acoustic effects of leading-edge serrations on airfoils[J].Journal of Aircraft,1974,11(4):197-202.
[13]Lee S.Reduction of blade-vortex interaction noise through porous leading edge[J].AIAA Journal,1994,32(3):480-488.
[14]Tinetti A F,Kelly J F,Thomas R H,et al.Reduction of wake-stator interaction noise using passive porosity,AIAA 2002-1036[R].Reston:AIAA,2012.
[15]Graham R R.The silent flight of owls[J].The Journal of the Royal Aeronautical Society,1934,38:837-843.
[16]Sun S M,Ren L Q,Xu C Y.Research on coupling sound absorption property of owl skin and feather[J].Noise and Vibration Control,2008,3:119-123(in Chinese).孙少明,任露泉,徐成宇.长耳鸮皮肤和覆羽耦合吸声降噪特性研究[J].噪声与振动控制,2008,3:119-123.
[17]Jacob M C,Boudet J,Casalino D,et al.A rod-airfoil experiment as benchmark for broadband noise modeling[J].Theoretical and Computational Fluid Dynamics,2005,19:171-196.
[18]Casalino D,Jacob M,Roger M.Prediction of rod-airfoil interaction noise using the Ffowcs-Williams-Hawkings analogy[J].AIAA,Journal,2003,41(2):182-191.
[19]Lorenzoni V,Moore P,Scarano F,et al.Aeroacoustic analysis of a rod-airfoil Flow by means of timeresolved PIV,AIAA 2009-3298[R].Reston:AIAA,2009.
[20]Moore P,Lorenzoni V,Scarano F.Two techniques for PIV-based aeroacoustic prediction and their application to a rod-airfoil experiment[J].Exp Fluids(2011)50:877-885.