Resolvent model for aeroacoustics of trailing edge noise

This study presents a physics-based, low-order model for the trailing edge (TE) noise generated by an airfoil at low angle of attack. The approach employs incompressible resolvent analysis of the mean flow to extract relevant spanwise-coherent structures in the transitional boundary layer and near w...

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Veröffentlicht in:	Theoretical and computational fluid dynamics 2024-04, Vol.38 (2), p.163-183
Hauptverfasser:	Demange, S., Yuan, Z., Jekosch, S., Hanifi, A., Cavalieri, A. V. G., Sarradj, E., Kaiser, T. L., Oberleithner, K.
Format:	Artikel
Sprache:	eng
Schlagworte:	Acoustics Aeroacoustics Airfoils Angle of attack Boundary layer transition Boundary layers Classical and Continuum Physics Compressibility Computational Science and Engineering Directivity Engineering Engineering Fluid Dynamics First principles Fluid flow High frequencies Incompressible flow Large eddy simulation Noise Original Article Physics Pressure Proper Orthogonal Decomposition Sound fields Structures Trailing edges
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