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Monday, July 8 • 16:30 - 16:50
MEASUREMENT OF TRAILING EDGE NOISE FROM A HEAVING AIRFOIL

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The trailing edge noise from a heaving wing with a constant NACA 0012 airfoil section was studied at a Reynolds number of 198000 using an anechoic wind tunnel. The airfoil was fixed at an incident angle of 0 degrees. The heaving frequency and amplitude were selected as 8Hz and 10mm, corresponding to a reduced frequency of 0.08 and a Strouhal number of 0.008 based on the chord length. A microphone array was utilized to detect the position and the strength of the noise source at different frequencies. For a stationary wing, the source strength of the broadband noise spreads evenly across the whole wing span while the source of the discrete tones appears as a pair of spanwise cells symmetrical about the spanwise centre. Short-time Fourier transform and a wavelet-based real-time beam-forming algorithm were used to analyse the time dependence of the sound spectra and the source strength in one heaving period, respectively. The sound pressure levels of the discrete tones increases while the wing passing over the mean phase position and experiencing the largest effective angle of attack, and it is attributed to the enhancement of the source strength at the corresponding time.

Moderators
KH

Kaveh Habibi

Sr. Aeroacoustics Engineer, Siemens Gamesa Renewable Energy
LM

Luc Mongeau

Prof., McGill University
MR

Michel Roger

Professeur, Ecole Centrale de Lyon

Authors

Monday July 8, 2019 16:30 - 16:50 EDT
St-Laurent 6
  T03 Aero… aircrft noise & vibr., RS01 Aeroacoustics