Spectral features of the wall-pressure fluctuations in turbulent wall flows with and without perturbations using LES

Viazzo, Stéphane; Dejoan, Anne; Schiestel, Roland

doi:10.1016/s0142-727x(00)00074-6

Cited by 43 publications

(23 citation statements)

References 23 publications

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“…This is coherent with the picture of smaller scales closer to the wall. Similar results are also reported in the analysis of the LES of incompressible channel flow by Viazzo et al (2001). These authors reported a peak value around ωδ * /U ∞ ≈0.3, which is also detectable in the present study, and is also in qualitative agreement with the experiments of Blake (1970).…”

Section: Wall Pressure Coherencesupporting

confidence: 92%

“…The model proposed by Viazzo where the mean value along the computational domain is used for Re τ (≃ 560), which yields 2.15. A still lower value of 1.9 is given in the simulations of incompressible channel flow at Re τ ≃ 400 by Kim (1989) (DNS) and at Re τ ≃ 640 by Viazzo et al (2001) …”

Section: Frequency Power Spectrum and Mean Square Pressurementioning

confidence: 88%

“…and large-eddy simulations (LES) of channel flow has been investigated in the past by Kim (1989), Choi & Moin (1990), Chang et al (1999), Viazzo et al (2001), or Hu et al (2006b. Furthermore, simplified semi-empirical models of wall-pressure fluctuations have been proposed.…”

Section: Wall Pressurementioning

confidence: 99%

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Turbulent boundary-layer noise: direct radiation at Mach number 0.5

Gloerfelt

Berland

2013

J. Fluid Mech.

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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. 2 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.

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Section: Wall Pressure Coherencesupporting

confidence: 92%

Section: Frequency Power Spectrum and Mean Square Pressurementioning

confidence: 88%

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Turbulent boundary-layer noise: direct radiation at Mach number 0.5

Gloerfelt

Berland

2013

J. Fluid Mech.

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“…As highlighted in table 3(a), the strongest discrepancy is found at the lowest Re τ . This result suggests that at such low Reynolds number the coherence decay becomes too abrupt (Viazzo, Dejoan & Schiestel 2001) for the results at the lowest Re τ to be relevant for practical applications.…”

Section: Resultsmentioning

confidence: 98%

Wall pressure coherence in supersonic turbulent boundary layers

et al. 2013

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"A numerical database (Bernardini & Pirozzoli, Phys. Fluids, vol. 23, 2011, 085102) is analysed to investigate cross-statistics of wall-pressure fluctuations induced by supersonic turbulent boundary layers developing over a rigid smooth wall without a pressure gradient. The Mach number spans from 2 to 4 and a relatively large range of Reynolds numbers is considered. It is shown, for the first time, that the cross-statistics of wall-pressure fluctuations at such high Mach numbers is very similar to that usually observed in incompressible flow conditions. Furthermore, it is demonstrated that theoretical predictions provided by the well-known Corcos and Efimtsov models continue to apply.

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“…In the directions parallel to the wall, values of about Δr ≃ rΔθ ≃ 30 are found for the four jets. Those values are similar to those used in the literature for the LES of turbulent boundary layers [28][29][30]. In the direction normal to the wall, values Δz ≃ 5 are used.…”

Section: B Numerical Parametersmentioning

confidence: 99%