Influence of curvature distribution smoothing on the reduction of aerofoil self-noise

Purpose This paper aims to investigate the influence of smooth curvature distributions on self-noise a low Reynolds number aerofoil and unveil flow mechanisms in phenomenon. Design/methodology/approach In this paper, large Eddy simulation (LES) approach was performed unsteady aerodynamic performance both original E387 redesigned A7 time-dependent study boundary layer characteristics at 100,000 angle attack (AoA) 4-degree. The is from by removing irregularities surface keeping nearly identical geometry. Flow vorticity magnitude aerofoils, along with spectra vertical fluctuating velocity component noise level, are analysed demonstrate bubble flapping process near trailing edge (TE) vortex shedding Findings provides quantitative insights about how laminar separation (LSB) within TE affects self-noise. It found that presents 10% smaller LSB compared AoA LES results also suggest distribution smoothing leads 6.5% reduction overall broadband level. Originality/value fulfils an identified need reveal unknown structure resulted phenomenon yielded smoothing.