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

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