Abstract In this contribution, a hybrid zonal simulation tool with volumetric inflow turbulence forcing is applied to trailing-edge noise of a NACA0012 airfoil with and without a porous insert at representative Mach and Reynolds number of 0.1118 and 1.0 × 106, respectively. The governing equations constitute the non-linear perturbation equations with viscous terms (i.e., the full Navier–Stokes equations), in which the porous material is modelled by a volume-averaged approach. Generic simulations with a single vortex passing the trailing edge revealed the expected noise reduction as well as an additional noise source. This new source originates from the turbulent flow passing the transition from solid to porous surface and was shown to increase significantly with increasing permeability. 3D simulations with a solid and porous trailing-edge showed good agreement with experimental aerodynamic and aeroacoustic validation data. The application of porous material to trailing-edge noise confirms the results reported in literature and underlines the validity of the porous model as well as it illustrates possible applications.

中文翻译：

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一种带多孔模型的后缘噪声区域噪声预测方法

摘要 在这篇文章中，具有体积流入湍流力的混合区域模拟工具分别应用于具有和不具有多孔插入件的 NACA0012 翼型的后缘噪声，其代表性马赫数和雷诺数分别为 0.1118 和 1.0 × 106。控制方程构成具有粘性项的非线性扰动方程（即完整的 Navier-Stokes 方程），其中多孔材料通过体积平均方法建模。单个涡流通过后缘的通用模拟揭示了预期的降噪以及额外的噪声源。这种新的来源源于湍流从固体表面到多孔表面的过渡，并且随着渗透率的增加而显着增加。具有实心和多孔后缘的 3D 模拟显示与实验空气动力学和空气声学验证数据非常吻合。将多孔材料应用于后缘噪声证实了文献中报告的结果，并强调了多孔模型的有效性，并说明了可能的应用。