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A rod-airfoil experiment as a benchmark for broadband noise modeling

机译：机翼型机翼实验作为宽带噪声建模的基准

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摘要

A low Mach number rod-airfoil experiment is shown to be a good benchmark for numerical and theoretical broadband noise modeling. The benchmarking approach is applied to a sound computation from a 2D unsteady-Reynolds-averaged Navier - Stokes (U-RANS) flow field, where 3D effects are partially compensated for by a spanwise statistical model and by a 3D large eddy simulation. The experiment was conducted in the large anechoic wind tunnel of the Ecole Centrale de Lyon. Measurements taken included particle image velocity (PIV) around the airfoil, single hot wire, wall pressure coherence, and far field pressure. These measurements highlight the strong 3D effects responsible for spectral broadening around the rod vortex shedding frequency in the subcritical regime, and the dominance of the noise generated around the airfoil leading edge. The benchmarking approach is illustrated by two examples:- the validation of a stochastical noise generation model applied to a 2D U-RANS computation;- the assessment of a 3D LES computation using a new subgrid scale (SGS) model coupled to an advanced-time Ffowcs-Williams and Hawkings sound computation.In both cases, the ability of computational fluid dynamics to model the source mechanisms and of the CAA approach to predict the far field are assessed separately.
机译：低马赫数的杆翼型实验被证明是数值和理论宽带噪声建模的良好基准。将基准测试方法应用于通过二维非稳态雷诺平均Navier-Stokes（U-RANS）流场进行的声音计算中，其中的3D效果可通过展向统计模型和3D大涡模拟来部分补偿。该实验是在里昂中央大学的大型消声风洞中进行的。所进行的测量包括机翼周围的粒子图像速度（PIV），单根热丝，壁压力相干性和远场压力。这些测量结果突出了强大的3D效应，该效应导致了在亚临界状态下杆涡旋脱落频率附近的光谱展宽，并且在翼型前缘周围产生的噪声占主导地位。通过两个示例说明了基准测试方法：-验证了应用于2D U-RANS计算的随机噪声生成模型;-使用结合了先进时间的新子网格规模（SGS）模型对3D LES计算进行评估Ffowcs-Williams和Hawkings的声音计算。在这两种情况下，都分别评估了计算流体动力学对源机制进行建模的能力以及CAA方法预测远场的能力。

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