Wall-resolved large eddy simulation for aeroengine aeroacoustic investigation

Lin, Yujing; Vadlamani, Rao; Savill, Mark; Tucker, Paul

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dc.contributor.author	Lin, Yujing
dc.contributor.author	Vadlamani, Rao
dc.contributor.author	Savill, Mark
dc.contributor.author	Tucker, Paul
dc.date.accessioned	2017-06-28T09:42:28Z
dc.date.available	2017-06-28T09:42:28Z
dc.date.issued	2017-06-22
dc.identifier.citation	Yujing Lin, Rao Vadlamani, Mark Savill, Paul Tucker, Wall-resolved large eddy simulation for aeroengine aeroacoustic investigation, Aeronautical Journal, Volume 121, Issue 1242, pp1032-1050	en_UK
dc.identifier.issn	0001-9240
dc.identifier.uri	http://dx.doi.org/10.1017/aer.2017.54
dc.identifier.uri	https://dspace.lib.cranfield.ac.uk/handle/1826/12119
dc.description.abstract	The work presented here forms part of a larger project on Large-Eddy Simulation (LES) of aeroengine aeroacoustic interactions. In this paper, we concentrate on LES of near-field flow over an isolated NACA0012 aerofoil at zero angle-of-attack and a chord based Reynolds number of Rec = 2 × 105. A wall-resolved compressible Numerical Large Eddy Simulation (NLES) approach is employed to resolve streak-like structures in the near-wall flow regions. The calculated unsteady pressure/velocity field will be imported into an analyticallybased scheme for far-field trailing-edge noise prediction later. The boundary-layer mean and root-mean-square (rms) velocity profiles, the surface pressure fluctuation over the aerofoil, and the wake flow development are compared with experimental data and previous computational simulations in our research group. It is found that the results from the wall-resolved compressible NLES are very encouraging as they correlate well with test data. The main features of the wall-resolved compressible NLES, as well as the advantages of such compressible NLES over previous incompressible LES performed in our research group, are also discussed. This paper will be presented at the ISABE 2017 Conference, 5-8 September 2017, Manchester, UK.	en_UK
dc.language.iso	en	en_UK
dc.publisher	Cambridge University Press	en_UK
dc.rights	Attribution-Non-Commercial 4.0 (CC BY-NC 4.0) You are free to: Share — copy and redistribute the material in any medium or format, Adapt — remix, transform, and build upon the material. The licensor cannot revoke these freedoms as long as you follow the license terms. Under the following terms: Attribution — You must give appropriate credit, provide a link to the license, and indicate if changes were made. You may do so in any reasonable manner, but not in any way that suggests the licensor endorses you or your use. Information: Non-Commercial — You may not use the material for commercial purposes. No additional restrictions — You may not apply legal terms or technological measures that legally restrict others from doing anything the license permits.
dc.subject	aeroacoustics	en_UK
dc.subject	NLES	en_UK
dc.title	Wall-resolved large eddy simulation for aeroengine aeroacoustic investigation	en_UK
dc.type	Article	en_UK