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- W2185044915 abstract "Our recent numerical and experimental efforts are reviewed examining flow-acoustic resonant interactions in transitional airfoil boundary layers and means of control of the resulting prominent, tonal trailing-edge noise sources. Experimentally recorded unsteady responses of loaded, transitional NACA0012 airfoil reveal operational regimes characterized by the presence of the shifted ladder-type tonal structures with dual velocity dependence observed in the surface pressure and the acoustic signals. High-fidelity numerical efforts employ a 6 th -order Navier-Stokes solver implementing a low-pass filtering of poorly resolved high-frequency solution content to retain numerical accuracy and stability over a range of transitional flow regimes. 2D and 3D (ILES) numerical experiments investigate the behavior of the boundary-layer statistical moments during the transitional flow regimes characterized by the presence of separation regions and the resulting formation of the highly-amplified instability waves scattered into noise at the airfoil trailing edge, thus triggering and sustaining the acoustic feedback-loop process. The current paper particularly focuses on the sensitivity of the airfoil flow-acoustic interactions (and the resulting acoustic signature) to the upstream flow conditions." @default.
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- W2185044915 date "2014-01-01" @default.
- W2185044915 modified "2023-10-12" @default.
- W2185044915 title "Analysis and Control of Flow-Acoustic Feedback-Loop Interactions in Transitional Airfoils" @default.
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