Journal article

Trailing-edge broadband noise prediction of an airfoil with boundary-layer tripping

J Winkler, H Wu, S Moreau, T Carolus, RD Sandberg

Journal of Sound and Vibration | Elsevier | Published : 2020


Hybrid methods for trailing edge noise prediction are applied to a NACA 6512-63 airfoil at zero angle of attack embedded in the actual narrow stream of the Siegen open-jet anechoic wind-tunnel. Incompressible large-eddy simulations (LES) of the airfoil trailing-edge flow yield the noise sources, and different analytical acoustic analogies then predict the acoustic far-field pressure. The chord-based Reynolds number of 1.9 × 105 triggers long laminar flow regions along the airfoil, leading to instability waves with an associated broadband noise radiation. To avoid this laminar-instability noise, the airfoil boundary layer is experimentally tripped on both sides. The actual serration tripping ..

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University of Melbourne Researchers


Awarded by German Research Foundation (DFG)

Awarded by German Academic Exchange Service (DAAD)

Awarded by EPSRC

Funding Acknowledgements

The authors gratefully acknowledge the financial and technical support received to conduct this study. This work was sponsored in part by the NSERC Discovery Grants Program of Canada, the HPC-Europa2 Program, the German Research Foundation (DFG) under grant WI-3501/1-1, and the German Academic Exchange Service (DAAD) under grant D/10/45322. The computationswere performed on the JHF cluster at Stanford University, the RUBENS cluster at Universitat Siegen, the MAMMOUTH-MP2 cluster at Universite de Sherbrooke (managed by Compute Canada/Calcul Quebec), and the UK Supercomputer HECToR. Computing time on HECToR was provided through the UK turbulence consortium under EPSRC grant EP/G069581/1.