Experience gained from previous jet noise studies with the unstructured large-eddy simulation flow solver “Charles” is summarized and put to practice for the predictions of supersonic jets issued from a converging–diverging round nozzle. In this work, the nozzle geometry is explicitly included in the computational domain using an unstructured body-fitted mesh. Two different mesh topologies are investigated, with emphasis on grid isotropy in the acoustic source-containing region, either directly or through the use of adaptive refinement, with grid size ranging from 42 to $55 \times 10^{6}$ control volumes. Three different operating conditions are considered: isothermal ideally expanded (fully expanded jet Mach number of $M_{j} = 1.5$ , temperature of $T_{j} / T_{\infty} = 1$ , and Reynolds number of ${R e}_{j} = 300, 000$ ), heated ideally expanded ( $M_{j} = 1.5$ , $T_{j} / T_{\infty} = 1.74$ , and ${R e}_{j} = 155, 000$ ), and heated overexpanded ( $M_{j} = 1.35$ , $T_{j} / T_{\infty} = 1.85$ , and ${R e}_{j} = 130, 000$ ). Blind comparisons with the available experimental measurements carried out at the United Technologies Research Center for the same nozzle and operating conditions are presented. The results show good agreement for both the flow and sound fields. In particular, the spectra shape and levels are accurately captured in the simulations for both near-field and far-field noise. In these studies, sound radiation from the jet is computed using an efficient permeable formulation of the Ffowcs Williams–Hawkings equation in the frequency domain. Its parallel implementation is reviewed and parametric studies of the far-field noise predictions are presented. As an additional step toward best practices for jet aeroacoustics with unstructured large-eddy simulations, guidelines and suggestions for the mesh design, numerical setup, and acoustic postprocessing steps are discussed.

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Volume 55, Number 4April 2017

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Copyright © 2016 by G. A. Brès, F. E. Ham, J. W. Nichols, and S. K. Lele. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0001-1452 (print) or 1533-385X (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.

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Acknowledgments

This work was supported by U.S. Navy Naval Air Systems Command (grant N68335-11-C-0026) under the supervision of John Spyropoulos. The simulations were performed as part of the High Performance Computing Challenge Project “Large Eddy Simulations of Supersonic Jet Noise and Combustor and Augmentor Spray Atomization.” The majority of the calculations were carried out on CRAY XE6 machines at the U.S. Department of Defense supercomputer facilities in the Engineer Research and Development Center and the U.S. Air Force Research Laboratory. The authors would like to thank Robert Schlinker, John Simonich, and Ramons Reba of United Technologies Research Center for providing the nozzle geometry, the experimental results, and conducting the blind comparisons.

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Received3 February 2016
Accepted12 September 2016
Published online12 January 2017

Unstructured Large-Eddy Simulations of Supersonic Jets

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