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Wall-resolved large eddy simulation for aeroengine aeroacoustic investigation

Part of: ISABE 2017

Published online by Cambridge University Press:  22 June 2017

Y. Lin ,
R. Vadlamani ,
M. Savill  and
P. Tucker
Y. Lin*
Affiliation:
Kingston University, London, UK
R. Vadlamani
Affiliation:
Cambridge University Engineering Department, Cambridge, UK
M. Savill
Affiliation:
Cranfield University, Cranfield, UK
P. Tucker
Affiliation:
Cambridge University Engineering Department, Cambridge, UK
*
*y.lin@kingston.ac.uk
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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.

Keywords

aeroacousticsNLES
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Special Issue 1242: The International Society of Air-breathing Engines (ISABE) 2017 Conference Special Issue , August 2017 , pp. 1032 - 1050
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This paper will be presented at the ISABE 2017 Conference, 3-8 September 2017, Manchester, UK.

References

REFERENCES

1. Ray, P.K. and Dawes, W.N. Detached-eddy simulation of transonic flow past a fan-blade section, 15th AIAA/CEAS Aeroacoustics Conference, 11-13 May, 2009, Miami, FL, US, AIAA 2009-3221.Google Scholar
2. Sagrado, A.G., Hynes, T. and Hodson, H. Experimental investigation into trailing edge noise sources, 12th AIAA/CEAS Aeroacoustics Conference, 8-10 May 2006, Cambridge, MA, US, AIAA 2006-2476.Google Scholar
3. Ghosal, S. An analysis of numerical errors in large-eddy simulations of turbulence, J Comput. Phys., 1996, 125, pp 187-206.CrossRefGoogle Scholar
4. Chow, F.K. and Moin, P. A further study of numerical errors in large-eddy simulations, J Comput. Phys., 2003, 184, pp 366-380.CrossRefGoogle Scholar
5. Sagrado, A.G. Boundary layer and trailing edge noise sources, PhD Thesis, 2007, Cambridge University, Cambridge, England.Google Scholar
6. Urange, A., Persson, P., Drela, M. and Peraire, J. Implicit large eddy simulation of transitional flows over airfoils and wings, 19th AIAA Computational Fluid Dynamics Conference, 2009, San Antonio, Texas, US, AIAA 2009-4131.Google Scholar
7. Herr, M., Ewert, R., Rautmann, C., Kamruzzaman, M., Bekiropoulos, D., Arina, R., Iob, A., Batten, P., Chakravarthy, S. and Bertagnolio, F. Broadband trailing-edge noise predictions-overview of BANC-III results, 21st AIAA/CEAS Aeroacoustics Conference, 2015, AIAA Aviation, AIAA 2015-2847, 2015.CrossRefGoogle Scholar
8. Wolf, W.R. and Lele, S.K. Trailing-edge noise predictions using compressible large-eddy simulation and acoustic analogy, AIAA J, 2012, 50, (11), pp 2423-2434.CrossRefGoogle Scholar
9. Gloerfelt, X. and Le Garrec, T. Trailing edge noise from an isolated aerofoil at a high reynolds number, 15th AIAA/CEAS Aeroacoustics Conference, (30th AIAA Aeroacoustics Conference), 11-13 May 2009, Miami, Florida, US, AIAA 2009-3201.Google Scholar
10. Manoha, E., Troff, B. and Sagaut, P. Trailing-edge noise prediction using large-eddy simulation and acoustic analogy, AIAA J, 2000, 38, (4), pp 575-583.CrossRefGoogle Scholar
11. Moreau, S., Christophe, J. and Roger, M. LES of the trailing-edge flow and noise of a NACA0012 aerofoil near stall, Proceedings of the Summer Program 2008, Center for Turbulence Research, 2008, pp 317-329.Google Scholar
12. Kojima, R., Nonomura, T., Oyama, A. and Fujii, K. Large-eddy simulation of low-Reynolds-number flow over thick and thin NACA airfoils, J Aircraft, 2013, 50, (1), pp 187-196.CrossRefGoogle Scholar
13. Li, Q., Peake, N. and Savill, M. Large eddy simulations for Fan-OGV broadband noise prediction, 14th AIAA/CEAS Aeroacoustics Conference, 5-7 May, 2008, Vancouver, Canada, AIAA 2008-2843.CrossRefGoogle Scholar
14. Li, Q., Peake, N. and Savill, M. Grid-refined LES predictions for Fan-OGV broadband noise, 15th AIAA/CEAS Aeroacoustics Conference, 11-13 May, 2009, Miami, Florida, US, AIAA 2009-3147.Google Scholar
15. Lin, Y., Savill, M., Vadlamani, N.R. and Loveday, R.J. Wall-resolved large eddy simulation over NACA0012 airfoil, Int J Aerospace Sciences, 2013, 2, (4), pp 149-162.Google Scholar
16. Hatman, A. and Wang, T. Separated-flow transition. Part 2 - Experimental results. ASME Paper No. 98-GT-462, 1998.Google Scholar
17. Blake, W.K. Mechanics of flow induced sound and vibration. Volume I (General Concepts and Elementary Sources) and Volume II (Complex Flow-Structure Interactions). Applied Mathematics and Mechanics Volume 17-I and Volume 17-II, 1986.Google Scholar
18. Choi, H. and Moin, P. Grid-point requirements for large eddy simulation: Chapman's estimates revisited, Center for Turbulence Research Annual Research Briefs, 2011, pp 31-36.Google Scholar
19. Young, A.D. Boundary Layers, 1989, BSP Professional Books.Google Scholar
20. Hatman, A. and Wang, T. Separated-flow transition. Part 1 - Experimental methodology and mode classification. ASME Paper No. 98-GT-461, 1998.Google Scholar
21. Stieger, R.D. The effects of wakes on separating boundary layers in low pressure turbines, PhD thesis, University of Cambridge, 2002.Google Scholar
22. Walker, G.J. Transitional flow in axial turbomachine blading, AIAA J., 1989, 27, (5), pp 595-602 CrossRefGoogle Scholar
23. Szawerdo, Z. Large eddy simulation of the NACA0012 airfoil trailing edge flow and noise, MSc Thesis, Cranfield University, Cranfield, UK, 2013.Google Scholar
24. Brooks, T.F., Pope, D.S. and Marcolini, M.A. Airfoil self-noise and prediction, Technical Report, NASA Reference Publication 1218, 1989.Google Scholar
25. Oerlemans, S. and Migliore, P. Aeroacoustic wind tunnel tests of wind turbine airfoils, AIAA Paper 2004-3042, 2004.Google Scholar
26. Roger, M. and Moreau, S. Broadband self-noise from loaded fan blades, AIAA J., 2004, 42, (3), pp 536-544.Google Scholar