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- W3189476432 abstract "This paper investigates the TNO type models for predicting the surface pressure spectrum underneath the turbulent boundary layer, which is considered the acoustic source for trailing edge noise. Two airfoil test cases, namely, NACA0015 and NACA0012, have been investigated using the flow solutions obtained from RANS and XFOIL at various Reynolds number and attack angles. Airfoil boundary layer flows are strongly influenced by the pressure gradient’s existence, the influence of which has been accounted for in this paper by improving the previously published anisotropic stretching coefficient definition. Additionally, we introduce the influence of pressure gradient in the velocity spectrum by scaling the integral correlation length with the kinematic shape factor. We apply this new approach and present a new model which fully accounts for pressure gradient and frequency dependency in the velocity spectrum. The predictions of the new model are in good agreement with the published experimental results." @default.
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- W3189476432 date "2021-07-28" @default.
- W3189476432 modified "2023-10-02" @default.
- W3189476432 title "Comparative Analysis of Low Order Wall Pressure Spectrum Models for Trailing Edge Noise Based in Amiet Theory" @default.
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- W3189476432 doi "https://doi.org/10.2514/6.2021-2231" @default.
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