Journal article

Different noise generation mechanisms of a controlled diffusion aerofoil and their dependence on Mach number

Mathieu Deuse, Richard D Sandberg

Journal of Sound and Vibration | Elsevier BV | Published : 2020


The self-noise of an isolated controlled-diffusion aerofoil is investigated using direct noise computations. The high-order finite difference solver HiPSTAR is used to conduct four large eddy simulations and one direct numerical simulation. The motivation is to investigate the multiple sources of aerofoil self-noise on a realistic compressor blade geometry, the physical mechanisms leading to the generation of sound, and the influence of compressibility effects. The angle of attack is 8°, the chord-based Reynolds number is 105, and results obtained for four values of the free-stream Mach number [0.2, 0.3, 0.4, 0.5] are compared. For those flow parameters, the pressure side is fully laminar, w..

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University of Melbourne Researchers


Awarded by Australian Research Council

Funding Acknowledgements

The authors are grateful for the funding provided by the Australian Research Council, Discovery Project Grant #DP180100898. The first author acknowledges the University of Melbourne for funding his PhD. This work was supported by resources provided by the Pawsey Supercomputing Centre with funding from the Australian Government and the Government ofWestern Australia. This project was undertaken with the assistance of resources and services from the National Computational Infrastructure (NCI), which is supported by the Australian Government. 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).