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首页> 外文会议>AIAA/CEAS aeroacoustics conference;AIAA aviation forum >Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Kevlar-Wall Low-Speed Wind Tunnel
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Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Kevlar-Wall Low-Speed Wind Tunnel

机译：JAXA Kevlar-Wall低速风洞中30P30N三元高升翼型翼型板条噪声的实验研究

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摘要

Aeroacoustic measurements associated with noise radiation from the leading-edge slat of the canonical, unswept 30P30N three-element high-lift airfoil configuration have been obtained in a 2 m x 2 m Kevlar-wall wind tunnel at the Japan Aerospace Exploration Agency (JAXA). Performed as part of a collaborative effort on airframe noise between JAXA and the National Aeronautics and Space Administration (NASA), the model geometry and majority of instrumentation details are identical to a NASA model with the exception of a larger span. The measurements have been designed to provide an important component of the dataset for Category 7 of the AIAA workshops on Benchmark problems for Airframe Noise Computations (BANC) and, more generally, an improved understanding and characterization of the noise source mechanisms associated with a leading-edge slat. Following the first phase of measurements at the Hard-wall test section in 2013 to obtain reliable near-field data with quasi-two-dimensional near-field characteristics, the second phase of measurements has been performed to obtain more reliable dataset of the acoustic data and the data with higher angles of attack where no significant narrowband peaks (NBPs) are observed in the spectra. The results in the Kevlar-wall wind tunnel exhibit better quantitative surface pressure spectra as well as the acoustic spectra obtained by integrating the noise source maps. The directivity characteristic of acoustic spectra obtained by the phased-microphone array is also shown.
机译：在日本航空航天局（JAXA）的2 m x 2 m凯夫拉尔壁风洞中，获得了与规范的，未扫掠的30P30N三元素高升力机翼配置的前沿板条的噪声辐射相关的航空声学测量。作为JAXA与美国国家航空航天局（NASA）之间的机体噪声协作努力的一部分，除了较大跨度外，模型的几何形状和大部分仪器细节均与NASA模型相同。这些测量旨在为AIAA关于飞机噪声计算基准问题（BANC）的基准问题的AIAA研讨会第7类提供数据集的重要组成部分，并且更广泛地讲，它可以更好地理解和表征与领先的噪声相关的噪声源机制，边缘板条。继2013年在硬壁测试部分进行第一阶段测量以获取具有准二维近场特性的可靠近场数据之后，已进行了第二阶段测量以获取更可靠的声波数据集以及具有较高攻角的数据，其中在光谱中未观察到明显的窄带峰（NBP）。凯夫拉尔墙风洞中的结果显示出更好的定量表面压力谱以及通过整合噪声源图获得的声谱。还显示了由相控麦克风阵列获得的声谱的方向性特征。

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