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首页> 外文会议>AIAA/CEAS aeroacoustics conference;AIAA aviation forum >Experimental and Numerical Analysis of the Aerodynamic and Aeroacoustic Properties of a 2D High-Lift Wing Model
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Experimental and Numerical Analysis of the Aerodynamic and Aeroacoustic Properties of a 2D High-Lift Wing Model

机译：二维高升力机翼模型的空气动力学和空气声学特性的实验和数值分析

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摘要

Aerodynamic and acoustic measurements of a 2D high-lift wing-section in flap full span deployed and flap side-edge (half span deployed) configurations are investigated both experimentally and numerically to understand the acoustic noise characteristics and the mechanisms of noise generation presented both in the slat and flap side-edge. Experimental analysis is carried out at the LAE-1 closed test section wind-tunnel and measured data includes phased array beamforming results along with steady pressure and hot-film anemometry measurements while numerical analysis using the PowerFLOW® software intends to replicate wind-tunnel conditions with hard-wall boundaries and results from both aerodynamic unsteadiness and far field predictions are presented. The high-lift model is a 2D wing model with single slotted flaps and slats. Tests were conducted both in full deployed flap or in half stowed configuration, for flap side-edge noise analysis. Results provide also comparisons between numerical and experimental data for steady aerodynamic data regarding surface pressure and flap side-edge vortex measurements along with unsteady aerodynamic measurements taken from hot-film anemometry performed at the slat in both chordwise and spanwise directions and far field acoustic noise predictions.
机译：在襟翼全跨展开和襟翼侧边缘（半跨展开）构型中二维高升力机翼截面的空气动力学和声学测量均通过实验和数值研究进行了研究，以了解声噪声特征和产生噪声的机理。板条和襟翼的侧边缘。实验分析是在LAE-1封闭测试区的风洞中进行的，测量数据包括相控阵波束成形结果以及稳定压力和热膜风速测量，而使用PowerFLOW®软件进行的数值分析则旨在复制风洞条件，包括：给出了硬壁边界以及空气动力学不稳定和远场预测的结果。高升力模型是具有单个开槽襟翼和板条的2D机翼模型。测试是在完全展开的襟翼或半收起状态下进行的，以分析襟翼的侧边缘噪声。结果还提供了数值和实验数据之间的比较，这些数据是关于表面压力和襟翼侧边缘涡旋测量的稳定空气动力学数据，以及沿翼片方向和翼展方向在板条上进行的热膜风速测量获得的非稳定空气动力学测量结果以及远场声噪声预测。

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