Conference Proceedings

Resolvent analysis-based pressure modeling for trailing edge noise prediction

Georges A Wagner, Mathieu Deuse, Simon J Illingworth, Richard D Sandberg

American Institute of Aeronautics and Astronautics | Published : 2019


This paper presents the first development steps of a hybrid computational aeroacoustics (CAA) method for the prediction of trailing edge (TE) noise, based on a physics-driven prediction of the surface pressure on an airfoil. Starting frommean flowdata for a given configuration, the dominant pressure modes over a foil are modeled with an incompressible formulation of the resolvent method. As a conceptual test of its suitability to predict surface pressures, the framework is used to model the unsteady surface pressure fluctuations generated by instability waves on an infinite flat plate. While a canonical test case, the flat plate is a good starting point for the investigation of airfoil TE no..

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Awarded by Australian Research Council

Funding Acknowledgements

G.A.Wagner thanks Sean Symon and Bo Jin for their help and guidance, as well as the University of Melbourne for a Melbourne Research Scholarship. The authors are grateful for the funding provided by the Australian Research Council, Discovery Project Grant #DP180100898. This work was also partly funded by the U.S. Office of Naval Research Global (ONR Global) under NICOP Grant N62909-17-1-2083. We gratefully acknowledge the support from Dr. Ki-Han Kim (ONG), and Dr. Sung-Eun Kim (ONR Global, Tokyo).

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