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1. C. K. W. Tam, “ Discrete tones of isolated airfoils,” J. Acoust. Soc. Am. 55, 11731177 (1974).
2. H. Arbey and J. Bataille, “ Noise generated by airfoil profiles placed in a uniform laminar flow,” J. Fluid Mech. 134, 3347 (1983).
3. D. J. Moreau, L. A. Brooks, and C. J. Doolan, “ On the aeroacoustic tonal noise generation mechanism of a sharp-edged plate,” J. Acoust. Soc. Am. 129, EL154EL160 (2011).
4. A. McAlpine, E. C. Nash, and M. V. Lowson, “ On the generation of discrete frequency tones by the flow around an aerofoil,” J. Sound Vib. 222, 753779 (1999).
5. C. K. W. Tam and H. Ju, “ Aerofoil tones at moderate Reynolds number,” J. Fluid Mech. 690, 536570 (2012).
6. K. L. Schumacher, C. J. Doolan, and R. M. Kelso, “ The effect of a cavity on airfoil tones,” J. Sound Vib. 333, 19131931 (2014).
7. M. J. Kingan and J. R. Pearse, “ Laminar boundary layer instability noise produced by an aerofoil,” J. Sound Vib. 322, 808828 (2009).
8. T. P. Chong and P. Joseph, “  ‘Ladder’ structure in tonal noise generated by laminar flow around an airfoil,” J. Acoust. Soc. Am. 131, EL461EL467 (2012).
9. T. F. Brooks, M. A. Marcolini, and D. S. Pope, “ Airfoil trailing edge flow measurements,” AIAA J. 24, 12451251 (1986).
10. R. W. Paterson, P. G. Vogt, M. R. Fink, and C. L. Munch, “ Vortex noise of isolated airfoils,” J. Aircraft 10, 296302 (1973).
11. V. Sarohia, “ Experimental investigation of oscillations in flows over shallow cavities,” AIAA J. 15, 984991 (1977).

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The response of the boundary layer over an airfoil with cavity to external acoustic forcing, across a sweep of frequencies, was measured. The boundary layer downstream of the cavity trailing edge was found to respond strongly and selectively at the natural airfoil tonal frequencies. This is considered to be due to enhanced feedback. However, the shear layer upstream of the cavity trailing edge did not respond at these frequencies. These findings confirm that an aeroacoustic feedback loop exists between the airfoil trailing edge and a location near the cavity trailing edge.


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