The effect of acoustic forcing on an airfoil tonal noise mechanism

dc.contributor.author	Schumacher, K.
dc.contributor.author	Doolan, C.
dc.contributor.author	Kelso, R.
dc.date.issued	2014
dc.description.abstract	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.
dc.description.statementofresponsibility	Karn L. Schumacher, Con J. Doolan, and Richard M. Kelso
dc.identifier.citation	Journal of the Acoustical Society of America, 2014; 136(2):EL78-EL83
dc.identifier.doi	10.1121/1.4885485
dc.identifier.issn	0001-4966
dc.identifier.issn	1520-8524
dc.identifier.orcid	Kelso, R. [0000-0002-5783-9232]
dc.identifier.uri	http://hdl.handle.net/2440/93650
dc.language.iso	en
dc.publisher	Acoustical Society of America
dc.rights	© 2014 Acoustical Society of America
dc.source.uri	https://doi.org/10.1121/1.4885485
dc.title	The effect of acoustic forcing on an airfoil tonal noise mechanism
dc.type	Journal article
pubs.publication-status	Published

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