30P30N翼型前缘缝翼远场噪声特性实验研究
详细信息 查看官网全文
- 英文论文题名：Experimental study of far-field radiated noise characteristic for the leading edge slat of 30P30N airfoil
- 论文作者：耿欣 ; 刘沛清 ; 郭昊 ; 田云
- 英文论文作者：Geng Xin ; Liu Peiqing ; Tian Yun ; Guo Hao ; School of Aeronautic Science and Engineering ; Beihang University
- 年：2016
- 作者机构：北京航空航天大学航空科学与工程学院;
- 论文关键词：前缘缝翼 ; 远场气动噪声 ; Kevlar实验段 ; 噪声频谱特性 ; 离散纯音噪声
- 英文论文关键词：the leading edge slat ; far-field noise ; Kevlar-walled test section ; noise spectrum characteristics ; discrete tones
- 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：V211.74
- 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：12
- 文件大小：2593k
- 原文格式：D
- 会议级别：全国
摘要
针对高升力翼型中前缘缝翼的远场气动噪声问题,本文以BANC-Ⅱ的30P30N标模为实验模型,在北京航空航天大学D5气动声学风洞开展实验研究,并采用新型的Kevlar壁面闭口实验段设计,可以对大尺寸多段翼构型在真实雷诺数下的气动参数和远场噪声同时进行测量。保持缝翼完全展开、襟翼处于收回的状态,改变实验段风速和构型迎角以获取不同工况下翼型表面压力分布和远场声压信号,经过快速傅里叶变换得到缝翼远场噪声频谱特性及其随来流风速、翼型攻角的变化规律。实验结果表明:频谱曲线中均存在离散纯音噪声,与缝翼凹腔自激振荡的预测纯音频率能够较好吻合,进一步验证了缝翼噪声中纯音的产生机理与缝翼凹腔内剪切层引起的的反馈回路有密切联系;远场气动噪声近似与来流速度的四次方成正比,离散纯音尖频随来流风速的增加会整体向右平移,且纯音频率基本不受迎角变化的影响,但尖频幅值会随攻角的增大显著降低。
To study the far-field aerodynamic noise of the leading edge slat of high-lift airfoil configuration, the experimental investigation of the BANC-Ⅱ/30P30N airfoil model was carried out in D5 areo-acoustic wind tunnel at Beihang University.A novel Kevlar-walled closed test section design has been applied, which was envisaged as a way of upgrading the capabilities of a conventional aerodynamic wind tunnel to include far-field acoustic measurements for larger model at real Reynolds numbers.The flap was retracted and the slat was deployed to isolate slat noise from other possible sources, the surface pressure distribution and the far-field sound pressure signals under different operating conditions were obtained by varying flow speed and angle of attack in the test section.The slat noise spectrum characteristics and the dependence of far-field noise on free stream velocity and airfoil incidence angle were acquired with the fast Fourier transform.The experimental results validated that the spectra are characterized by several tonal peaks, the tonal frequencies could agree well with the prediction obtained using the theoretical relationship of selfsustained oscillation in slat cove, therefore support the fact that the feedback loop generated by the shear layer originating from the slat cusp seems to be the main physical mechanism involved in the occurrence of tonal noise.The farfield noise generated from the slat was proportional to the four power of flow speed, the tonal frequencies would shift toward higher frequencies with increasing free steam velocity.However, the frequencies wasn't influenced by the varied angle of attack, but the amplitude of the frequencies decreased significantly with increasing angle of attack.
To study the far-field aerodynamic noise of the leading edge slat of high-lift airfoil configuration, the experimental investigation of the BANC-Ⅱ/30P30N airfoil model was carried out in D5 areo-acoustic wind tunnel at Beihang University.A novel Kevlar-walled closed test section design has been applied, which was envisaged as a way of upgrading the capabilities of a conventional aerodynamic wind tunnel to include far-field acoustic measurements for larger model at real Reynolds numbers.The flap was retracted and the slat was deployed to isolate slat noise from other possible sources, the surface pressure distribution and the far-field sound pressure signals under different operating conditions were obtained by varying flow speed and angle of attack in the test section.The slat noise spectrum characteristics and the dependence of far-field noise on free stream velocity and airfoil incidence angle were acquired with the fast Fourier transform.The experimental results validated that the spectra are characterized by several tonal peaks, the tonal frequencies could agree well with the prediction obtained using the theoretical relationship of selfsustained oscillation in slat cove, therefore support the fact that the feedback loop generated by the shear layer originating from the slat cusp seems to be the main physical mechanism involved in the occurrence of tonal noise.The farfield noise generated from the slat was proportional to the four power of flow speed, the tonal frequencies would shift toward higher frequencies with increasing free steam velocity.However, the frequencies wasn't influenced by the varied angle of attack, but the amplitude of the frequencies decreased significantly with increasing angle of attack.
引文
[1]Crighton,D.,“Aeroacoustics of Flight Vehicles:Theory and Practice.Volume 1:Noise Sources,”NASA Langley Research Center TR-90-3052,Hampton,VA,Aug.1991.
[2]张卫民,郝璇,陈大斌,等.大型客机气动噪声预测[J].航空制造技术,2010(14):66-69.Zhang W M,Hao X,Chen D B,et al.Aeroacoustic Prediction of Large Commercial Aircraft[J].Aeronautical Ma-nufacturing Technology,2010(14):66-69.(in Chinese).
[3]Werner Dobrzynski."Almost 40 Years of Airframe Noise Research:What Did We Achieve?"Journal of Aircraft,Vol.47,No.2(2010),pp.353-367.
[4]Carlos C.Pagani,Jr.,Daniel S.Souza,and Marcello A.F.Medeiros."Slat Noise:Aeroacoustic Beamforming in Closed-Section Wind Tunnel with Numerical Comparison",AIAA Journal,Vol.54,No.7(2016),pp.2100-2115.
[5]K.Takeda,X.Zhang,and P.Nelson."Unsteady aerodynamics and aeroacoustics of a high-lift device configuration",40th AIAA Aerospace Sciences Meeting&Exhibit,Aerospace Sciences Meetings,(AIAA-2002-0570)
[6]K.Takeda,G.Ashcroft,X.Zhang,and P.Nelson."Unsteady aerodynamics of slat cove flow in a high-lift device configuration",39th Aerospace Sciences Meeting and Exhibit,Aerospace Sciences Meetings,(AIAA-2001-0706)
[7]Meelan M.Choudhari and Mehdi R.Khorrami."Effect of Three-Dimensional Shear-Layer Structures on Slat Cove Unsteadiness",AIAA Journal,Vol.45,No.9(2007),pp.2174-2186.
[8]M.Terracol,E.Manoha,and B.Lemoine."Investigation of the Unsteady Flow and Noise Generation in a Slat Cove",AIAA Journal,Vol.54,No.2(2016),pp.469-489.
[9]乔渭阳,Michel U.二维传声器阵列测量技术及其对飞机进场过程着陆噪声的实验研究[J].声学学报,2001,26(2):162-168.QIAO Weiyang,Michel U.A study on landing aircraft noise based on the fly-over measurements with a planar microphone array[J].Acta Acustica,2001,26(2):162-168.(in Chinese)
[10]李强,陈迎春,李亚林,等.民用飞机增升装置气动噪声学风洞试验初步研究[J].民用飞机设计与研究.2013(3):6-11.Li Q,Chen Y C,Li Y L,et al.Preliminarily Investigation on High Lift System Aerodynamic Noise in Wind Tunnel Tests of Civil Aircraft[J].Civil Aircraft Design and Research,2013(3):6-11.(in Chinese)
[11]刘志仁,王福新,宋文滨,等.二维增升装置前缘缝翼的远场噪声分析[J].空气动力学学报.2012,30(03):388-393.LIU Zhiren,WANG Fuxin,SONG Wenbin,et al.Farfield aeroacoustic analysis for slat of a two-dimensional high-lift configuration[J].ACTA Aerodynamica Sinica,2012,30(03):388-393.(in Chinese)
[12]卢清华,陈宝.基于LES方法的增升装置气动噪声特性分析[J].空气动力学学报.2016,34(04):448-455.Lu Qinghua,Chen Bao.Analysis of aeroacoustics characteristics of high lift device using LES method[J].ACTA Aerodynamica Sinica,2016,34(04):448-455.(in Chinese)
[13]Mitsuhiro Murayama,Kazuyuki Nakakita,Kazuomi Yamamoto,Hiroki Ura,Yasushi Ito,and Meelan M.Choudhari."Experimental Study on Slat Noise from30P30N Three-Element High-Lift Airfoil at JAXAHard-Wall Lowspeed Wind Tunnel",20th AIAA/CEASAeroacoustics Conference,AIAA Aviation,(AIAA2014-2080)
[14]Ben Smith,Hugo Camargo,Ricardo Burdisso,and William Devenport."Development and Testing of a Novel Acoustic Wind Tunnel Concept",11th AIAA/CEASAeroacoustics Conference,Aeroacoustics Conferences,(AIAA-2005-3053)
[15]W.J.Devenport,R.A.Burdisso,A.Borgoltz,P.A.Ravetta,M.F.Barone,K.A.Brown,M.A.Morton,The Kevlar-walled anechoic wind tunnel,Journal of Sound and Vibration332(2013)3971-3991.
[16]Dobrzynski,W.,and Pott-Pollenske,M.,“Slat Noise Source Studies for Farfield Noise Prediction,”7th AIAA/CEAS Aeroacoustics Conference and Exhibit,AIAA Paper 2001-2158,June 2001.
[17]Y.P.Guo,K.J.Yamamoto,and R.W.Stoker."Component-Based Empirical Model for High-Lift System Noise Prediction",Journal of Aircraft,Vol.40,No.5(2003),pp.914-922.
[18]Choudhari,M.,Khorrami,M.,Lockard,D.,Atkins,H.,and Lilley,G.,“Slat Cove Noise Modeling:A Posteriori Analysis of Unsteady RANS Simulations,”8th AIAA/CEAS Aeroacoustics Conference&Exhibit,AIAA Paper 2002-2468,June 2002.
[19]Y.P.Guo and M.C.Joshi."Noise Characteristics of Aircraft High Lift Systems",AIAA Journal,Vol.41,No.7(2003),pp.1247-1256.
[20]Mendoza,F.,and Brooks,T.,“Aeroacoustic Measurements of a Wing/Slat Model,”8th AIAA/CEAS Aeroacoustics Conference&Exhibit,AIAA Paper 2002-2604,June 2002.
[21]Taro Imamura,Hiroki Ura,Yuzuru Yokokawa,and Kazuomi Yamamoto."A Far-field Noise and Nearfield Unsteadiness of a Simplified High-liftconfiguration Model(Slat)",47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition,Aerospace Sciences Meetings,(AIAA-2009-1239)
[22]Kolb,A.,Faulhaber,P.,Drobietz,R.,and Grunewald,M.,“Aeroacoustic Wind Tunnel Measurements on a 2DHigh-Lift Configuration,”13th AIAA/CEAS Aeroacoustics Conference,AIAA Paper 2007-3447,May2007.
[23]Paterson,R.W.,Vogt,P.G.,and Fink,M.R.,“Vortex Noise of Isolated Airfoils,”Society of Naval Architects and Marine Engineers,and U.S.Navy,Advanced Marine Vehicles Meeting,AIAA Paper 1972-0656,1972.
[24]Tam,C.K.W.,“Discrete Tones of Isolated Airfoils,”Journal of the Acoustical Society of America,Vol.55,No.6,1974,pp.1173-1177.
[25]Arbey,H.,and Bataille,J.,“Noise Generated by Airfoil Profiles Placed in a Uniform Laminar Flow,”Journal of Fluid Mechanics,Vol.134,No.1,1983,pp.33-47.
[26]Lowson,M.V.,Fiddes,S.P.,and Nash,E.C.,“Laminar Boundary Layer Aero-Acoustic Instabilities,”32nd Aerospace Sciences Meeting and Exhibit,AIAA Paper1994-0358,1994.
[27]Lowson,M.V.,Mc Alpine,A.,and Nash,E.C.,“The Generation of Boundary Layer Instability Noise on Aerofoils,”36th AIAA Aerospace Sciences Meeting and Exhibit,AIAA Paper 1998-0627,1998.
[28]Desquesnes,G.,Terracol,M.,and Sagaut,P.,“Numerical Investigation of the Tone Noise Mechanism over Laminar Airfoils,”Journal of Fluid Mechanics,Vol.591,Nov.2007,pp.155-182.
[29]Makiya,S.,Inasawa,A.,and Asai,M.,“Vortex Shedding and Noise Radiation from a Slat Trailing Edge,”AIAA Journal,Vol.48,No.2,2010,pp.502-509.
[30]Pott-Pollenske,M.,Alvarez-Gonzalez,J.,and Dobrzynski,W.,“Effect of Slat Gap on Farfield Radiated Noise and Correlation with Local Flow Characteristics,”9th AIAA/CEAS Aeroacoustics Conference,AIAA Paper2003-3228,2003.
[31]Roger,M.,and Pérennès,S.,“Low-Frequency Noise Sources in Two-Dimensional High-Lift Devices,”5th AIAA/CEAS Aeroacoustics Conference,AIAA Paper2000-1972,2000.
[32]Rossiter,J.E.,“Wind Tunnel Experiments of the Flowover Rectangular Cavities at Subsonic and Transonic Speeds,”Ministry of Aviation;Royal Aircraft Establishment;RAE Farnborough,1964.
[33]Block,P.J.W.,“Noise Response of Cavities of Varying Dimensions at Subsonic Speeds,”NASA TN-D-8351,1976.
[2]张卫民,郝璇,陈大斌,等.大型客机气动噪声预测[J].航空制造技术,2010(14):66-69.Zhang W M,Hao X,Chen D B,et al.Aeroacoustic Prediction of Large Commercial Aircraft[J].Aeronautical Ma-nufacturing Technology,2010(14):66-69.(in Chinese).
[3]Werner Dobrzynski."Almost 40 Years of Airframe Noise Research:What Did We Achieve?"Journal of Aircraft,Vol.47,No.2(2010),pp.353-367.
[4]Carlos C.Pagani,Jr.,Daniel S.Souza,and Marcello A.F.Medeiros."Slat Noise:Aeroacoustic Beamforming in Closed-Section Wind Tunnel with Numerical Comparison",AIAA Journal,Vol.54,No.7(2016),pp.2100-2115.
[5]K.Takeda,X.Zhang,and P.Nelson."Unsteady aerodynamics and aeroacoustics of a high-lift device configuration",40th AIAA Aerospace Sciences Meeting&Exhibit,Aerospace Sciences Meetings,(AIAA-2002-0570)
[6]K.Takeda,G.Ashcroft,X.Zhang,and P.Nelson."Unsteady aerodynamics of slat cove flow in a high-lift device configuration",39th Aerospace Sciences Meeting and Exhibit,Aerospace Sciences Meetings,(AIAA-2001-0706)
[7]Meelan M.Choudhari and Mehdi R.Khorrami."Effect of Three-Dimensional Shear-Layer Structures on Slat Cove Unsteadiness",AIAA Journal,Vol.45,No.9(2007),pp.2174-2186.
[8]M.Terracol,E.Manoha,and B.Lemoine."Investigation of the Unsteady Flow and Noise Generation in a Slat Cove",AIAA Journal,Vol.54,No.2(2016),pp.469-489.
[9]乔渭阳,Michel U.二维传声器阵列测量技术及其对飞机进场过程着陆噪声的实验研究[J].声学学报,2001,26(2):162-168.QIAO Weiyang,Michel U.A study on landing aircraft noise based on the fly-over measurements with a planar microphone array[J].Acta Acustica,2001,26(2):162-168.(in Chinese)
[10]李强,陈迎春,李亚林,等.民用飞机增升装置气动噪声学风洞试验初步研究[J].民用飞机设计与研究.2013(3):6-11.Li Q,Chen Y C,Li Y L,et al.Preliminarily Investigation on High Lift System Aerodynamic Noise in Wind Tunnel Tests of Civil Aircraft[J].Civil Aircraft Design and Research,2013(3):6-11.(in Chinese)
[11]刘志仁,王福新,宋文滨,等.二维增升装置前缘缝翼的远场噪声分析[J].空气动力学学报.2012,30(03):388-393.LIU Zhiren,WANG Fuxin,SONG Wenbin,et al.Farfield aeroacoustic analysis for slat of a two-dimensional high-lift configuration[J].ACTA Aerodynamica Sinica,2012,30(03):388-393.(in Chinese)
[12]卢清华,陈宝.基于LES方法的增升装置气动噪声特性分析[J].空气动力学学报.2016,34(04):448-455.Lu Qinghua,Chen Bao.Analysis of aeroacoustics characteristics of high lift device using LES method[J].ACTA Aerodynamica Sinica,2016,34(04):448-455.(in Chinese)
[13]Mitsuhiro Murayama,Kazuyuki Nakakita,Kazuomi Yamamoto,Hiroki Ura,Yasushi Ito,and Meelan M.Choudhari."Experimental Study on Slat Noise from30P30N Three-Element High-Lift Airfoil at JAXAHard-Wall Lowspeed Wind Tunnel",20th AIAA/CEASAeroacoustics Conference,AIAA Aviation,(AIAA2014-2080)
[14]Ben Smith,Hugo Camargo,Ricardo Burdisso,and William Devenport."Development and Testing of a Novel Acoustic Wind Tunnel Concept",11th AIAA/CEASAeroacoustics Conference,Aeroacoustics Conferences,(AIAA-2005-3053)
[15]W.J.Devenport,R.A.Burdisso,A.Borgoltz,P.A.Ravetta,M.F.Barone,K.A.Brown,M.A.Morton,The Kevlar-walled anechoic wind tunnel,Journal of Sound and Vibration332(2013)3971-3991.
[16]Dobrzynski,W.,and Pott-Pollenske,M.,“Slat Noise Source Studies for Farfield Noise Prediction,”7th AIAA/CEAS Aeroacoustics Conference and Exhibit,AIAA Paper 2001-2158,June 2001.
[17]Y.P.Guo,K.J.Yamamoto,and R.W.Stoker."Component-Based Empirical Model for High-Lift System Noise Prediction",Journal of Aircraft,Vol.40,No.5(2003),pp.914-922.
[18]Choudhari,M.,Khorrami,M.,Lockard,D.,Atkins,H.,and Lilley,G.,“Slat Cove Noise Modeling:A Posteriori Analysis of Unsteady RANS Simulations,”8th AIAA/CEAS Aeroacoustics Conference&Exhibit,AIAA Paper 2002-2468,June 2002.
[19]Y.P.Guo and M.C.Joshi."Noise Characteristics of Aircraft High Lift Systems",AIAA Journal,Vol.41,No.7(2003),pp.1247-1256.
[20]Mendoza,F.,and Brooks,T.,“Aeroacoustic Measurements of a Wing/Slat Model,”8th AIAA/CEAS Aeroacoustics Conference&Exhibit,AIAA Paper 2002-2604,June 2002.
[21]Taro Imamura,Hiroki Ura,Yuzuru Yokokawa,and Kazuomi Yamamoto."A Far-field Noise and Nearfield Unsteadiness of a Simplified High-liftconfiguration Model(Slat)",47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition,Aerospace Sciences Meetings,(AIAA-2009-1239)
[22]Kolb,A.,Faulhaber,P.,Drobietz,R.,and Grunewald,M.,“Aeroacoustic Wind Tunnel Measurements on a 2DHigh-Lift Configuration,”13th AIAA/CEAS Aeroacoustics Conference,AIAA Paper 2007-3447,May2007.
[23]Paterson,R.W.,Vogt,P.G.,and Fink,M.R.,“Vortex Noise of Isolated Airfoils,”Society of Naval Architects and Marine Engineers,and U.S.Navy,Advanced Marine Vehicles Meeting,AIAA Paper 1972-0656,1972.
[24]Tam,C.K.W.,“Discrete Tones of Isolated Airfoils,”Journal of the Acoustical Society of America,Vol.55,No.6,1974,pp.1173-1177.
[25]Arbey,H.,and Bataille,J.,“Noise Generated by Airfoil Profiles Placed in a Uniform Laminar Flow,”Journal of Fluid Mechanics,Vol.134,No.1,1983,pp.33-47.
[26]Lowson,M.V.,Fiddes,S.P.,and Nash,E.C.,“Laminar Boundary Layer Aero-Acoustic Instabilities,”32nd Aerospace Sciences Meeting and Exhibit,AIAA Paper1994-0358,1994.
[27]Lowson,M.V.,Mc Alpine,A.,and Nash,E.C.,“The Generation of Boundary Layer Instability Noise on Aerofoils,”36th AIAA Aerospace Sciences Meeting and Exhibit,AIAA Paper 1998-0627,1998.
[28]Desquesnes,G.,Terracol,M.,and Sagaut,P.,“Numerical Investigation of the Tone Noise Mechanism over Laminar Airfoils,”Journal of Fluid Mechanics,Vol.591,Nov.2007,pp.155-182.
[29]Makiya,S.,Inasawa,A.,and Asai,M.,“Vortex Shedding and Noise Radiation from a Slat Trailing Edge,”AIAA Journal,Vol.48,No.2,2010,pp.502-509.
[30]Pott-Pollenske,M.,Alvarez-Gonzalez,J.,and Dobrzynski,W.,“Effect of Slat Gap on Farfield Radiated Noise and Correlation with Local Flow Characteristics,”9th AIAA/CEAS Aeroacoustics Conference,AIAA Paper2003-3228,2003.
[31]Roger,M.,and Pérennès,S.,“Low-Frequency Noise Sources in Two-Dimensional High-Lift Devices,”5th AIAA/CEAS Aeroacoustics Conference,AIAA Paper2000-1972,2000.
[32]Rossiter,J.E.,“Wind Tunnel Experiments of the Flowover Rectangular Cavities at Subsonic and Transonic Speeds,”Ministry of Aviation;Royal Aircraft Establishment;RAE Farnborough,1964.
[33]Block,P.J.W.,“Noise Response of Cavities of Varying Dimensions at Subsonic Speeds,”NASA TN-D-8351,1976.