2018 AIAA/CEAS Aeroacoustics Conference最新文献_第10页

Experimental Investigation of Acoustical Coupling between Cavity Flow and Cross Cylinder Wake 空腔流与横柱尾流声学耦合的实验研究

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3471

Hao Guo, Xuan Liang, T. Hu, Peiqing Liu

引用次数: 0

Measurement of Flow Separation Noise on a Full-scale Wind Turbine 全尺寸风力机流动分离噪声的测量

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3462

S. Buck

引用次数: 3

The Dynamic Response of a Pinhole Microphone under Flows of Varying Shear Stress 变剪应力流动下针孔传声器的动态响应

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3933

N. A. Balantrapu, Russell J. Repasky, Liselle A. Joseph, W. Devenport

引用次数: 3

Acoustic beamforming array design using an iterative microphone removal method 基于迭代麦克风去除方法的声波束形成阵列设计

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2807

E. Arcondoulis, Yu Liu

引用次数: 3

Toward a Semi-Empirical Noise Prediction for Airfoils with Serrated Trailing Edges 带锯齿尾缘翼型的半经验噪声预测

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2813

Y. Mayer, B. Lyu, Hasan Kamliya Jawahar, M. Azarpeyvand

{"title":"Toward a Semi-Empirical Noise Prediction for Airfoils with Serrated Trailing Edges","authors":"Y. Mayer, B. Lyu, Hasan Kamliya Jawahar, M. Azarpeyvand","doi":"10.2514/6.2018-2813","DOIUrl":"https://doi.org/10.2514/6.2018-2813","url":null,"abstract":"© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. A novel serrated trailing edge (STE) noise prediction model has been implemented and applied successfully to realistic airfoils with straight and serrated trailing edges. This model has several advantages over Howe's model as it utilizes an iterative procedure to solve the governing partial differential equations as opposed to the diffraction Green's function. The new model also takes both destructive and constructive interferences into account and is also applicable to high Mach numbers. Both the TNO and Chase wavenumber-frequency models have been implemented as input to the STE noise prediction model. The necessary boundary layer input parameters can be obtained from experiments or standard computational fluid dynamics simulations. In this work, we have used RANS CFD simulations to obtain the boundary layer information needed for the TNO and Chase models. Far-field noise comparisons are provided between the STE model and experimental data. A study to determine the most suitable location over the serration area to extract the boundary layer parameters has also been conducted and the changes in the flow due to the presence of the serrations are investigated. Differences in the predicted far-field sound reduction of up to 5 dB have been found for different boundary layer extraction locations over the serration area. The implemented STE model has the potential to improve the current noise prediction capabilities, and thereby improve serration design.","PeriodicalId":429337,"journal":{"name":"2018 AIAA/CEAS Aeroacoustics Conference","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127824654","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6

Characterization of Liners using a Lattice-Boltzmann Solver 用格子-玻尔兹曼解算器表征线性线

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4192

P. Manjunath, F. Avallone, D. Casalino, D. Ragni, M. Snellen

引用次数: 7

Experimental Investigations on Noise Shielding: Dependency on Reference Noise Source and Testing Environment 噪声屏蔽实验研究:对参考噪声源和测试环境的依赖

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2820

Karl-Stéphane Rossignol, J. Delfs, M. Mößner, D. Gély, J. Bulté, F. Hutcheson

{"title":"Experimental Investigations on Noise Shielding: Dependency on Reference Noise Source and Testing Environment","authors":"Karl-Stéphane Rossignol, J. Delfs, M. Mößner, D. Gély, J. Bulté, F. Hutcheson","doi":"10.2514/6.2018-2820","DOIUrl":"https://doi.org/10.2514/6.2018-2820","url":null,"abstract":"This paper presents the experimental results of a study conducted at DLR, ONERA and NASA on the shielding of sound by an NACA 0012 airfoil. The work presented was done in the context of the AVT-233 working group of the Science and Technology Organization (STO) of NATO. The experiments were conducted in the DLR Acoustic Wind Tunnel Braunschweig (AWB), the ONERA F2 tunnel and the NASA Quiet Flow Facility (QFF), with the goal of investigating facility-to-facility effects on the collected data. Two impulsive source concepts were used in the course of these experiments, DLR’s laser sound source and ONERA’s electric discharge source (SPARC). The collected data reveal that the different tunnel environments do not strongly affect the results obtained with either source. The laser sound source is found to deliver consistent results in all three wind tunnels, for the 7, 14 and 28 kHz octave bands at M=0.0 and M=0.16. In the highest octave band considered (56 kHz), the results are found to be very sensitive to the choice of operating parameters. The SPARC source also delivered consistent results in the low frequency range, in both the F2 tunnel and the AWB, for both Mach numbers tested. This joint effort has led to the development of a highly valuable database for the validation of shielding prediction tools.","PeriodicalId":429337,"journal":{"name":"2018 AIAA/CEAS Aeroacoustics Conference","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133744142","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7

Trailing-edge noise in slowly-varying, sheared flow 慢变剪切流中的尾缘噪声

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2810

David I. Baker, N. Peake

引用次数: 3

Resonance and Tones in Dual-Stream Nozzles induced by vortex shedding from struts 支板旋涡脱落引起的双流喷嘴共振和音调

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3939

I. Milanović, K. Zaman, C. Miller

引用次数: 1

Flight and Ground Operations in Support of Airframe Noise Reduction Tests 支持机身降噪测试的飞行和地面操作

2018 AIAA/CEAS Aeroacoustics Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2970

E. Baumann, E. Waggoner

{"title":"Flight and Ground Operations in Support of Airframe Noise Reduction Tests","authors":"E. Baumann, E. Waggoner","doi":"10.2514/6.2018-2970","DOIUrl":"https://doi.org/10.2514/6.2018-2970","url":null,"abstract":"The National Aeronautics and Space Administration (NASA) Acoustic Research Measurements (ARM) project was established to evaluate via flight tests the noise reduction benefits of the Adaptive Compliant Trailing Edge (ACTE) technology along with various main landing gear noise reduction concepts. The ACTE replaces the original Fowler flaps on the NASA SubsoniC Research Aircraft Testbed (SCRAT), thus creating a seamless trailing edge that provides significant noise abatement benefits. The various main landing gear noise reduction concepts are grouped under the LAnding Gear noisE Reduction (LAGER) task and consist of fairings placed on the main landing gear along with two separate treatments applied to the main landing gear wheel well cavities. This paper discusses the tasks necessary to prepare each of these technologies for the ARM flights. The LAGER hardware was taken from model-scale concepts tested in wind tunnels to flight hardware, which had to be cleared as airworthy for the ARM flights. The ACTE flaps were initially intended to be removed from the SCRAT prior to the start of the ARM project. Retaining the ACTE flaps on the aircraft for a longer period of time to support the ARM flights resulted in additional inspections and considerations since the ACTE flaps were flown longer and at certain flight conditions for longer periods of time than initially analyzed. The flight and ground operations required for the ARM tests required extensive coordination among multiple groups and organizations in order to be successful. This paper provides an overview of the hardware development, ground operations, and flight operations which went into acquiring the desired acoustic measurements. In general, the flights were successful and demonstrated the noise reduction benefits of the ACTE flaps, the LAGER gear fairings, and the LAGER gear cavity treatments.","PeriodicalId":429337,"journal":{"name":"2018 AIAA/CEAS Aeroacoustics Conference","volume":"107 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131508443","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7