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Leading edge serrations for the reduction of aerofoil self-noise at low angle of attack, pre-stall and post-stall conditions

Lacagnina, G., Chaitanya, P., Kim, J. H. , Berk, T., Joseph, P., Choi, K. S., Ganapathisubramani, B., Hasheminejad, S. M., Chong, T. P., Stalnov, O., Shahab, M. F., Omidyeganeh, M. ORCID: 0000-0002-4140-2810 & Pinelli, A. ORCID: 0000-0001-5564-9032 (2021). Leading edge serrations for the reduction of aerofoil self-noise at low angle of attack, pre-stall and post-stall conditions. International Journal of Aeroacoustics, 20(1-2), pp. 130-156. doi: 10.1177/1475472x20978379


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 (Formula presented.). 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.

Publication Type: Article
Additional Information: © The Author(s) 2021.
Publisher Keywords: Stall noise, leading edge serrations, noise reductions, aerofoil self-noise
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics
Departments: School of Science & Technology > Engineering
SWORD Depositor:
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Available under License Creative Commons: Attribution International Public License 4.0.

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