On the effects of leading edge serrations on aeroacoustic properties during stall

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The effect of leading edge serrations on the surface pressure fluctuation spectra and boundary layer qualities of a NACA 0012 airfoil has been investigated experimentally, with an emphasis on reducing airfoil separation and stall noise. Five leading edge serration add-ons with various serration heights and wavelengths have been tested in conjunction with a highly instrumented NACA 0012 airfoil. It is shown that all serrations cause a significant increase in surface pressure fluctuation spectra in the pre-stall region. However, for angles of attack in the post-stall regime, surface pressure fluctuation spectra reductions of up to 15dB have been observed for some serrations. These surface pressure fluctuation spectra reductions have been linked to the changes observed in the complex flow-field near the trailing edge, namely boundary layer thickness and velocity fluctuation reductions, as a result of the counter-rotating vortex pairs generated by the respective serrations.
Original languageEnglish
Title of host publicationProceedings of the 23rd International Congress on Acoustics, integrating 4th EAA Euroregio 2019
EditorsMartin Ochmann
PublisherDEGA e.V.
Number of pages8
ISBN (Print)9783939296157
Publication statusPublished - 9 Sept 2019
Event23rd International Congress on Acoustics - Eurogress Aachen, Aachen, Germany
Duration: 9 Sept 201913 Sept 2019

Publication series

NameProceedings of the ICA AND EAA EUROREGIO
PublisherDEGA e.V.
ISSN (Print)2226-7808


Conference23rd International Congress on Acoustics
Abbreviated titleICA 2019
Internet address


  • leading edge serrations
  • separation and stall noise
  • flow control
  • surface pressure fluctuations
  • trailing edge noise


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