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Eddy viscosity for resolvent-based jet noise models

Pickering, Ethan and Rigas, Georgios and Colonius, Tim and Sipp, Denis and Schmidt, Oliver T. (2019) Eddy viscosity for resolvent-based jet noise models. In: 25th AIAA/CEAS Aeroacoustics Conference, 20-23 May 2019, Delft, Netherlands.

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Response modes computed via linear resolvent analysis have shown promising results for qualitatively modeling both the hydrodynamic and acoustic fields in jets when compared to data-deduced modes from high-fidelity, large-eddy simulations (LES). For an improved quantitative prediction of the near- and far-field, the role of Reynolds stresses must also be considered. In this study, we propose a methodology to deduce an eddy-viscosity model that optimally captures the nonlinear forcing of resolvent modes. The methodology is based on the maximization of the projection between resolvent analysis and spectral proper orthogonal decomposition (SPOD) modes using a Lagrangian optimization framework. For a Mach 0.4 round, isothermal, turbulent jet, four methods are used to increase the projection coefficients: linear damping, spatially constant eddy-viscosity field, a turbulent kinetic energy derived viscosity field, and an optimized eddy-viscosity field. The resulting projection coefficients for the optimized eddy-viscosity field between SPOD and resolvent can be increased to over 90% for frequencies in the range St = 0.35−1 with significant improvements to St < 0.35. We find that the use of a frequency-independent turbulent kinetic energy turbulent viscosity model produces modes closely inline with optimal results, providing a preliminary eddy-viscosity resolvent model for jets.

Item Type:Conference or Workshop Item (Paper)
Related URLs:
URLURL TypeDescription Paper Paper
Pickering, Ethan0000-0002-4485-6359
Rigas, Georgios0000-0001-6692-6437
Colonius, Tim0000-0003-0326-3909
Sipp, Denis0000-0002-2808-3886
Schmidt, Oliver T.0000-0002-7097-0235
Additional Information:© 2019 by The Authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Published Online: 18 May 2019. This research was supported by a grant from the Office of Naval Research (grant No. N00014-16-1-2445) with Dr. Steven Martens as program manager. E.P. was supported by the Department of Defense (DoD) through the National Defense Science Engineering Graduate Fellowship (NDSEG) Program. The LES study was performed at Cascade Technologies, with support from ONR and NAVAIR SBIR project, under the supervision of Dr. John T. Spyropoulos. The main LES calculations were carried out on DoD HPC systems in ERDC DSRC.
Funding AgencyGrant Number
Office of Naval Research (ONR)N00014-16-1-2445
National Defense Science and Engineering Graduate (NDSEG) FellowshipUNSPECIFIED
Naval Air Systems Command (NAVAIR)UNSPECIFIED
Subject Keywords:Aeroacoustics
Other Numbering System:
Other Numbering System NameOther Numbering System ID
AIAA Paper2019-2454
Record Number:CaltechAUTHORS:20190709-092102524
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:96981
Deposited By: Melissa Ray
Deposited On:12 Jul 2019 17:01
Last Modified:16 Nov 2021 17:25

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