D5气动声学风洞气动声学实验研究
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- 论文作者：刘沛清 ; 李玲 ; 邢宇 ; 郭昊
- 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：气动声学风洞 ; 起落架 ; 增升装置 ; 马赫数比例律 ; Kevalr布
- 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：11
- 文件大小：1026k
- 原文格式：D
- 会议级别：全国
摘要
本文介绍了在北京航空航天大学D5气动声学风洞进行的起落架及增升装置气动声学实验结果。对起落架的实验研究表明,起落架的远场噪声马赫数比例律存在双段标度特性,在低频部分马赫数比例律满足传统的六次方关系,但在高频部分则满足七次方关系。将轮胎内侧空腔结构填充后发现起落架的噪声能够降低2.5-3d B。对增升装置的实验研究表明,采用传统的开口试验段并不能很好地模拟翼型绕流特点,而采用Kevalr布和穿孔板相结合的试验段布局,则能保证流场相似性,同时也能测量远场噪声,因此适合于增升装置翼型的远场噪声测量。
引文
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[21]HUANG X,ZHANG X,LI Y.Broadband flow-induced sound control using plasma actuators[J].Journal of Sound and Vibration.2010,329:2477-2489.
[22]LI Y,ZHANG X,HUANG X.The use of plasma actuators for bluff body broadband noise control[J].Experiments in Fluids.2010,49:367-377.
[23]ANGLAND D,ZHANG X,GOODYER M.Use of Blowing Flow Control to Reduce Bluff Body Interaction Noise[J].AIAA Journal.2012,50(8):1670-1684.
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[43]Christodoulos Andreou,Will Graham,Ho-Chul Shin.Aeroacoustic Study of Airfoil Leading Edge HighLift Devices[J].AIAA-2006-2515.
[44]Christodoulos Andreou,Will Graham,Ho-Chul Shin.Aeroacoustic Comparison of Airfoil Leading Edge HighLift Geometries and Supports[J].AIAA-2007-230.
[45]S.Anders,W.Sellers III,A.Washburn.Active Flow Control Activities at NASA Langley[J].AIAA-2004-2623.
[46]Thomas F O,Kozlov A,Corke K C.Plasma actuators for cylinder flow control and noise reduction.AIAA J2008;46(8):1921-31.
[47]M.G.Smith,Leung Choi Chow.Attenuation of slat trailing edge noise using slat gap acoustic liners[J].AIAA-2006-2666.
[48]Choudhari,M.M.,and Khorrami,M.,―Computational Study of Porous Treatment for Altering Flap Side-Edge Flow Field,‖AIAA/Confederation of European Aerospace Societies Paper 2003-3113,May 2003.
[49]Angland,D.,Zhang,X.,Chow,L.C.,and Molin,N.,―Measurements of Flow Around a Flap Side-Edge with Porous Edge Treatment,‖AIAA Paper 2006-0213,Jan.2006.
[50]L.Koop,K.Ehrenfried,Reduction of flap side-edge noise:Passive and Active Flow Control[R],10th AIAA/CEAS Aeroacoustics Conference,2004
[51]Dobrzynski W,Bieler H,Chowm L C,Remy H.The airframe noise reduction challenge:lessons learned from the European Silencer Project.Braunschweig:Deutscher Luft-und Raumfahrt Kon-gress;2006
[52]Storms B,Hayes J,Jaeger S,Soderman P.Aeroacoustic study of flap-tip noise reduction using continuous moldline,technology.AIAA-2000-1976;2000.
[53]CASALINO D,RIBEIRO A F,FARES E.Facing rim cavities fluctuation modes[J].Journal of Sound and Vibration.2014,333:2812-2830.
[54]CASALINO D,RIBEIRO A F,FARES E.LatticeBoltzmann Aeroacoustic Analysis of the LAGOONLanding-Gear Configuration[J].AIAA Journal.2014,52(6):1232-1248.
[55]Reger R W,Cattafesta L N.Experimental Study of the Rudimentary Landing Gear Acoustics[J].AIAA Journal.2015,53(6):1715-1720.
[56]S.Jaeger,W.Horne,C.Allen,Effect of surface treatment on array microphone self-noise,in:6th Aeroacoustics Conference and Exhibit,12-14 June 2000,Lahaina,HI,AIAA paper 2000-1937,2000.
[57]Y.Guo,Slat noise modeling and prediction,J.Sound.Vib.331(15)(2012)3567-3586.
[58]A.Kolb,P.Faulhaber,R.Drobietz,M.Grnewald,Aeroacoustic Wind Tunnel Measurements on a 2D High-Lift Configuration,in:13th AIAA/CEAS Aeroacoustics Conference(28th AIAA Aeroa-coustics Conference),AIAAPaper 2007-3447,2007.
[59]Rossiter,J.,Wind-Tunnel Experiments on the Flow over Rectangular Cavities at Subsonic and Transonic Speeds,Aeronautical Research Council Reports and Memoranda,1966.
[60]Rossiter,J.E.,Wind Tunnel Experiments of the Flow over Rectangular Cavities at Subsonic and Transonic Speeds,Ministry of Aviation;Royal Aircraft Establishment;RAE Farnborough,1964.
[2]LI Y,WANG X N,ZHANG D J.Control strategies for aircraft airframe noise reduction[J].Chinese Journal of Aeronautics,2013.26(2):249-260.
[3]朱自强,兰世隆.民机机体噪声及其降噪研究[J].航空学报,2015,36(2):406-421.ZHU Z Q,LAN S L.Study of airframe noise and its reduction for commercial aircraft[J].Acta Aeronautica et Astronautica Sinica.2015,36(2):406-421(in Chinese).
[4]LIU P Q,XING Y,GUO H,LI L.Design and performance of a small-scale aeroacoustic wind tunnel[J].Applied Acoustics.2017,116:65-69.
[5]T.Maeda,Y.Kondo,RTRI's Large-scale low-noise wind tunnel and wind tunnel tests[R],Quarterly Report of RTRI,Vol.42(2),2001,pp.65-70.
[6]Kim M,Lee J,Kee J,Chang J.Hyundai Full Scale Aero-acoustic Wind Tunnel[R].SAE Technical Papers.2001;2001-01-0629.
[7]Duell E,Yen J,Arnette S,Walter J.Recent Advances in Large Scale Aeroacoustic Wind Tunnels[R].2002.
[8]Pott-Pollenske M,Delfs J.Enhanced Capabilities of the Aeroacoustic Wind Tunnel Braunschweig[R].2008.
[9]Remillieux M,Crede E,Camargo H,et al.Calibration and Demonstration of the New Virginia Tech Anechoic Wind Tunnel[R].2008.
[10]HELLER H H,DOBRZYNSKI W M.Unsteady surface pressure characteristics on aircraft components and farfield radiated airframe noise[J].Journal of Aircraft,1978,l15:809-815.
[11]GUO Y P,YAMAMOTO K J,Stoker R W.Experimental study on aircraft landing gear noise[J].Journal of Aircraft,2006,43(2):306-317.
[12]LI Y,SMITH M,ZHANG X.Identification and Attenuation of a Tonal-Noise Source on an Aircraft’s Landing Gear[J].Journal of Aircraft,2010,47(3):796-804.
[13]LI Y,SMITH M,ZHANG X.Measurement and control of aircraft landing gear broadband noise[J].Aerospace Science and Technology,2012,23:213-223.
[14]YOKOKAWA Y,IMAMURA T,URA H,et al.Experimental Study on Noise Generation of a Two-Wheel Main Landing Gear.AIAA-2010-3973[R].Reston:AIAA 2010.
[15]Lazos B.S.Mean Flow Features Around the Inline Wheels of Four-Wheel Landing Gear[J].AIAA Journal.2002;40:193-8.
[16]乔渭阳,许开富,武兆伟,等.大型客机起飞着陆过程噪声辐射特性对比分析[J].航空学报,2008,29(3):534-541.QIAO W Y,XU K F,WU Z W,et al.Noise Radiation of Large-scale Commercial Aircraft in Take-off and Landing[J].Acta Aeronautica et Astronautica Sinica.2008,29(3):534-541(in Chinese).
[17]龙双丽,聂宏,薛彩军,等.飞机起落架气动噪声特性仿真与试验[J].航空学报,2012,33(6):1002-1013.LONG S L,NIE H,XUE C J,et al.Simulation and experiment on aeroacoustic noise characteristics of aircraft landing gear[J].Acta Aeronautica et Astronautica Sinica.2012,33(6):1002-1013(in Chinese).
[18]龙双丽,聂宏,薛彩军,等.民用飞机起落架气动噪声数值仿真[J].南京航空航天大学学报,2012,44(6):786-791.LONG S L,NIE H,XUE C J,et al.Aerodynamic Noise Simulation of Commercial Aircraft Landing Gear[J].Journal of Nanjing University of Aeronautics&Astronautics.2012,44(6):786-791(in Chinese).
[19]龙双丽,聂宏,薛彩军,等.某型飞机主起落架结构件气动噪声特性研究[J].振动与冲击.2013,32(1):134-139.LONG S L,NIE H,XUE C J,et al.Noise characteristics of an aircraft's main landing gear structure[J].Journal of Vibration and Shock.2013,32(1):134-139(in Chinese).
[20]MURAYAMA M,YOKOKAWA Y,YAMAMOTO K,et al.Computational study of low-noise fairings around tire-axle region of a two-wheel main landing gear[J].Computers&Fluids,2013,85:114-124.
[21]HUANG X,ZHANG X,LI Y.Broadband flow-induced sound control using plasma actuators[J].Journal of Sound and Vibration.2010,329:2477-2489.
[22]LI Y,ZHANG X,HUANG X.The use of plasma actuators for bluff body broadband noise control[J].Experiments in Fluids.2010,49:367-377.
[23]ANGLAND D,ZHANG X,GOODYER M.Use of Blowing Flow Control to Reduce Bluff Body Interaction Noise[J].AIAA Journal.2012,50(8):1670-1684.
[24]朱自强,陈迎春等.高升力系统外形的数值模拟计算[J].航空学报:2005,16(3):257-262.
[25]Bruce L.Storms,Julie A.Hayes,Patrick J.Moriarty,James C.Ross.Aeroacoustic Measurements Of Slat Noise on a Three-Dimensional High-Lift System[J].AIAA-1999-1957.
[26]Choudhari,M.,et al.Aeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel[J].NASATM-2002-211432,Feb.2002a.
[27]Daniel Konig,Seong R.Koh,Wolfgang Schroder,Matthias Meinke.Slat Noise Source Identification[J].AIAA-2009-3100.
[28]K.Takeda,X.Zhang,P.A.Nelson.Unsteady Aerodynamics and Aeroacoustics Of a High-Lift Device Configuration[J].AIAA-2002.
[29]SINGER,B.A,LOCKARD,D.P.,BRENTNER.Computational aeroacoustic analysis of slat trailing-edge flow[J].AIAA,2000,38(9):1558-1558.
[30]K.Takeda,G.B.Ashcroft,X.Zhang,et al..UNSTEADYAERODYNAMICS OF SLAT COVE FLOW IN AHIGH-LIFT DEVICE CONFIGURATION[J].AIAA-2001-0706.
[31]Mehdi R.Khorrami,M E.Berkman,Meelan Choudhari.Unsteady Flow Computations of a Slat with a Blunt Trailing Edge[J].AIAA-2000.
[32]Dobrzynski,W.,Nagakura,K.,Gehlhar,B.,Buschbaum.Airframe Noise Studies on Wings with Deployed HighLift Devices[J].AIAA-1998-2337.
[33]Paschal,K.,Jenkins,L.,Yao.Unsteady Slat Wake Characteristics of a 2-D High-Lift Configuration[J].AIAA-2000-0139.
[34]Meelan M.Choudhari,Mehdi R.Khorrami.Slat Cove Unsteadiness:Effect of 3D Flow Structures[J].AIAA-2006-0211.
[35]Robert G.Rackl,Gregory Miller,Yueping Guo,Kingo Yamamoto.Airframe Noise Studies-Review and Future Direction[J].NASA/CR,2005.
[36]Hardin J C,Noise radiation from the side edges of flaps,AIAA J.,1980
[37]Sanehiro Makiya,Ayumu Inasawa,Masahito Asai.Vortex Shedding and Noise Radiation from a Slat Trailing Edge[J].AIAA-2010.
[38]Tomoaki Ikeda.Self-Noise Effects on Aerodynamics of Cambered Airfoils at Low Reynolds Number.[C]:AIAAJOURNAL.2015.
[39]Choudhari,M.,et al.Aeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel[J].NASATM-2002-211432,Feb.2002a
[40]Mehdi R.Khorrami,M E.Berkman,Meelan Choudhari.Unsteady Flow Computations of a Slat with a Blunt Trailing Edge[J].AIAA-2000.
[41]Dobrzynski,W.,Nagakura,K.,Gehlhar,B.,Buschbaum.Airframe Noise Studies on Wings with Deployed HighLift Devices[J].AIAA-1998-2337.
[42]Mehdi R.Khorrami,David P.Lockard.EFFECTS OFGEOMETRIC DETAILS ON SLAT NOISEGENERATION AND PROPAGATION[J].AIAA-2006-2664.
[43]Christodoulos Andreou,Will Graham,Ho-Chul Shin.Aeroacoustic Study of Airfoil Leading Edge HighLift Devices[J].AIAA-2006-2515.
[44]Christodoulos Andreou,Will Graham,Ho-Chul Shin.Aeroacoustic Comparison of Airfoil Leading Edge HighLift Geometries and Supports[J].AIAA-2007-230.
[45]S.Anders,W.Sellers III,A.Washburn.Active Flow Control Activities at NASA Langley[J].AIAA-2004-2623.
[46]Thomas F O,Kozlov A,Corke K C.Plasma actuators for cylinder flow control and noise reduction.AIAA J2008;46(8):1921-31.
[47]M.G.Smith,Leung Choi Chow.Attenuation of slat trailing edge noise using slat gap acoustic liners[J].AIAA-2006-2666.
[48]Choudhari,M.M.,and Khorrami,M.,―Computational Study of Porous Treatment for Altering Flap Side-Edge Flow Field,‖AIAA/Confederation of European Aerospace Societies Paper 2003-3113,May 2003.
[49]Angland,D.,Zhang,X.,Chow,L.C.,and Molin,N.,―Measurements of Flow Around a Flap Side-Edge with Porous Edge Treatment,‖AIAA Paper 2006-0213,Jan.2006.
[50]L.Koop,K.Ehrenfried,Reduction of flap side-edge noise:Passive and Active Flow Control[R],10th AIAA/CEAS Aeroacoustics Conference,2004
[51]Dobrzynski W,Bieler H,Chowm L C,Remy H.The airframe noise reduction challenge:lessons learned from the European Silencer Project.Braunschweig:Deutscher Luft-und Raumfahrt Kon-gress;2006
[52]Storms B,Hayes J,Jaeger S,Soderman P.Aeroacoustic study of flap-tip noise reduction using continuous moldline,technology.AIAA-2000-1976;2000.
[53]CASALINO D,RIBEIRO A F,FARES E.Facing rim cavities fluctuation modes[J].Journal of Sound and Vibration.2014,333:2812-2830.
[54]CASALINO D,RIBEIRO A F,FARES E.LatticeBoltzmann Aeroacoustic Analysis of the LAGOONLanding-Gear Configuration[J].AIAA Journal.2014,52(6):1232-1248.
[55]Reger R W,Cattafesta L N.Experimental Study of the Rudimentary Landing Gear Acoustics[J].AIAA Journal.2015,53(6):1715-1720.
[56]S.Jaeger,W.Horne,C.Allen,Effect of surface treatment on array microphone self-noise,in:6th Aeroacoustics Conference and Exhibit,12-14 June 2000,Lahaina,HI,AIAA paper 2000-1937,2000.
[57]Y.Guo,Slat noise modeling and prediction,J.Sound.Vib.331(15)(2012)3567-3586.
[58]A.Kolb,P.Faulhaber,R.Drobietz,M.Grnewald,Aeroacoustic Wind Tunnel Measurements on a 2D High-Lift Configuration,in:13th AIAA/CEAS Aeroacoustics Conference(28th AIAA Aeroa-coustics Conference),AIAAPaper 2007-3447,2007.
[59]Rossiter,J.,Wind-Tunnel Experiments on the Flow over Rectangular Cavities at Subsonic and Transonic Speeds,Aeronautical Research Council Reports and Memoranda,1966.
[60]Rossiter,J.E.,Wind Tunnel Experiments of the Flow over Rectangular Cavities at Subsonic and Transonic Speeds,Ministry of Aviation;Royal Aircraft Establishment;RAE Farnborough,1964.
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