This paper addresses the usefulness of leading edge serrations for reducing aerofoil self-noise over a wide range of angles of attack. Different serration geometries are studied over a range of Reynolds number $(Re\approx 2·{10}^5-4·{10}^5)$. Design guidelines are proposed that permit noise reductions over most angles of attack. It is shown that serration geometries reduces the noise but adversely effect the aerodynamic performance suggesting that a trade-off should be sought between these two considerations. The self-noise performance of leading edge serrations has been shown to fall into three angle of attack (AoA) regimes: low angles where the flow is mostly attached, moderate angles where the flow is partially to fully separated, and high angles of attack where the flow is fully separated. Leading edge serrations have been demonstrated to be effective in reducing noise at low and high angles of attack but ineffective at moderate angles. The noise reduction mechanisms are explored in each of three angle regimes.

本文探讨了前缘锯齿状在减小大迎角范围内的翼型自噪声方面的作用。在雷诺数范围内研究了不同的锯齿几何形状$（\mathrm{[R}Ë\approx 2·{10}^5-4·{10}^5）$。提出了设计指南，允许在大多数迎角范围内降低噪声。结果表明，锯齿状的几何形状降低了噪音，但对空气动力学性能产生了不利影响，这表明应在这两个考虑之间进行权衡。前沿锯齿的自噪声性能已显示出可分为三种迎角（AoA）模式：气流主要附着在其中的低角度；气流部分完全分离的中等角度；以及迎角高的情况流被完全分离。前沿锯齿已被证明可有效降低低攻角和高攻角的噪声，但对中等角度则无效。在三种角度方案中的每一种中都探索了降噪机制。