2012
DOI: 10.1016/j.jsv.2011.09.019
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Direct simulations of trailing-edge noise generation from two-dimensional airfoils at low Reynolds numbers

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Cited by 41 publications
(21 citation statements)
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“…They also succeeded in suppressing trailing-edge noise using a thin plate attached to the trailing edge of the model, and observed naturally growing T-S waves with broadband characteristics, showing the existence of a feedback loop between unstable T-S waves in the boundary layer and trailing-edge noise. These observations also exhibit good agreement with the analytical results of McAlpine et al The existence of a feedback loop is also supported by several numerical simulations, namely those of Desquesnes et al 14) and Ikeda et al, 15) both of whom further pursued the idea that the most amplified wave is responsible for causing tone generation.…”
Section: Introductionsupporting
confidence: 80%
“…They also succeeded in suppressing trailing-edge noise using a thin plate attached to the trailing edge of the model, and observed naturally growing T-S waves with broadband characteristics, showing the existence of a feedback loop between unstable T-S waves in the boundary layer and trailing-edge noise. These observations also exhibit good agreement with the analytical results of McAlpine et al The existence of a feedback loop is also supported by several numerical simulations, namely those of Desquesnes et al 14) and Ikeda et al, 15) both of whom further pursued the idea that the most amplified wave is responsible for causing tone generation.…”
Section: Introductionsupporting
confidence: 80%
“…By using Eq. (1), ∆f = 0.42 corresponds to U c 0.47U ∞ , which is a little higher than U c /U ∞ 0.4 reported in [14] and also usually given by a linear stability analysis, but still in a reasonable range; the phase velocity U c 0.5U ∞ was reported in the two-dimensional calculation of NACA0006 airfoil at Re = 20, 000 [17]. The present observation strongly suggests the formation of a feedback loop mechanism.…”
Section: Acoustic Feedback Loop In Three-dimensional Fieldsmentioning
confidence: 57%
“…The transition of vortex shedding patterns due to the onset of an AFL, is well related with the difference of hydrodynamic instability mechanisms between wake and boundary layer [17]. Fig.…”
Section: Time-averaged Aerodynamic Forcesmentioning
confidence: 66%
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