Leading edge serrations for the reduction of aerofoil self-noise at low angle of attack, pre-stall and post-stall conditions
Leading edge serrations for the reduction of aerofoil self-noise at low angle of attack, pre-stall and post-stall conditions
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DOI：
10.1177/1475472x20978379
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发表时间：
2021-02-01
影响因子：
1
通讯作者：
Pinelli, Alfredo
中科院分区：
文献类型：
--
作者：
Lacagnina, Giovanni;Chaitanya, Paruchuri;Pinelli, Alfredo
本文论述了前缘锯齿在大迎角范围内降低翼型自噪声的有效性。不同的锯齿几何形状的范围内的雷诺数oRe类似于2类似于105类似于4类似于105索恩进行了研究。提出了允许在大多数迎角下降低噪声的设计准则。结果表明，锯齿形的几何形状降低了噪声，但对气动性能产生不利影响，这表明应该在这两个因素之间寻求折衷。前缘锯齿的自噪声性能已被证明落入三个攻角（AoA）区域：流动大部分附着的低角度、流动部分到完全分离的中等角度以及流动完全分离的高攻角。前缘锯齿已经被证明在低攻角和高攻角时能有效地降低噪声，但在中等攻角时无效。在三个角度制度的每一个探讨的降噪机制。
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 oRe similar to 2 similar to 105 similar to 4 similar to 105THORN. 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.