is an open access repository that collects the work of Arts et Métiers ParisTech researchers and makes it freely available over the web where possible.This is an author-deposited version published in: http://sam.ensam.eu Handle ID: .http://hdl.handle.net/10985/8636
To cite this version :Xavier GLOERFELT, Julien BERLAND -Turbulent boundary layer noise : direct radiation at Mach number 0.5 -Journal of Fluid Mechanics -Vol. 723, p.318-351 -2013 Any correspondence concerning this service should be sent to the repository Administrator : archiveouverte@ensam.euUnder consideration for publication in J. Fluid Mech.
1Turbulent boundary layer noise: direct radiation at Mach number 0.5 Boundary layers constitute a fundamental source of aerodynamic noise. A turbulent boundary layer over a plane wall can provide an indirect contribution to the noise by exciting the structure, and a direct noise contribution. The latter part can play a significant role even if its intensity is very low, explaining why it is hardly measured unambiguously.In the present study, the aerodynamic noise generated by a spatially developing turbulent boundary layer is computed directly by solving the compressible Navier-Stokes equations.This numerical experiment aims at giving some insight into the noise radiation character- The acoustic domain, corresponding to supersonic wavenumbers, is detectable but can † Present address: EDF R&D, MFEE, I84, 6 Quai Watier, 78400 Chatou, France.
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X. Gloerfelt and J. Berlandhardly be separated from the convective ridge at this relatively high speed. This is also due to the low frequencies of sound emission as noted previously.