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- W2045404727 abstract "An experimental and theoretical investigation has been carried out to further understand the tonal noise generation mechanism on aerofoils. Experiments were conducted on NACA 0012 aerofoil sections in a low-turbulence closed working section wind tunnel which was modified to approximate to anechoic conditions. Narrow band acoustic tones were observed up to 30dBs above background noise. High resolution flow velocity measurements have been made with a three component laser Doppler anemometer (LDA) which have revealed the presence of strongly amplified boundary layer instabilities in a region of separated shear flow just upstream of the pressure surface trailing edge. These instabilities match the frequency of the acoustic tone for each case and corresponding flow visualisation experiments have shown these instabilities to roll up to form a regular Karman type vortex street." @default.
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- W2045404727 date "1998-01-12" @default.
- W2045404727 modified "2023-09-24" @default.
- W2045404727 title "The generation of boundary layer instability noise on aerofoils" @default.
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- W2045404727 doi "https://doi.org/10.2514/6.1998-627" @default.
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