Recent Progress on MILES for High Reynolds Number Flows

[+] Author and Article Information
F. F. Grinstein

Naval Research Laboratory, Laboratory for Computational Physics and Fluid Dynamics, Code 6410, Washington, DC 20375-5344

C. Fureby

The Swedish Defence Research Agency, FOI, Department of Weapons and Protection, Warheads and Propulsion, SE-172 90, Stockholm, Sweden

J. Fluids Eng 124(4), 848-861 (Dec 04, 2002) (14 pages) doi:10.1115/1.1516576 History: Received March 11, 2002; Revised April 22, 2002; Online December 04, 2002
Copyright © 2002 by ASME
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TVD regions for first and second accurate TVD schemes together with selected limiters
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Time-averaged (or mean) velocity profiles 〈v̄1〉 normalized by the friction velocity uτt for fully developed turbulent channel flow at Ret=395 from MILES using different flux-limiters
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Flow visualizations of vortex-ring bifurcation phenomena for AR=4 jets; (a) elliptic cold jets (laboratory), 53 and (b) rectangular cold jets (MILES), 50. The flow direction is from bottom to top and time-sequences progress from left to right, in the numerical visualizations (based on isosurfaces of the vorticity magnitude); (c) sensitivity of vortex ring dynamics to jet initial conditions (Tj/Ta=1 in “cold” case, and Tj/Ta=5 in “hot” case); Re=Γ>90,000, and M=0.6, based on the circulation Γ of the initial vortex rings and transient jet velocity.
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Turbulent kinetic energy v̄1rms, normalized by the friction velocity uτ versus the wall-normal distance at Reτ=395 (blue), Reτ=2030 (green), and Reτ=10,000 (red) for all cases reported in Table 1; outer scaling is used at the horizontal axis
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Resolved Reynolds stress profiles 〈v1v2〉, normalized by the friction velocity uτ versus the wall-normal distance at Reτ=395 (blue), Reτ=2030 (green), and Reτ=10,000 (red) for all cases reported in Table 1; outer scaling is used at the horizontal axis
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Schematic of the Pitz-Daily backward-facing step configuration
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Visualization of the flowfield for the nonreacting case using contours of the instantaneous streamwise velocity component at the centerplane and iso-surfaces of the second invariant, Q, of the velocity gradient tensor
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Near-field MILES simulations of vortex-ring dynamics and associated sound generation in free jets emerging from rectangular nozzles, 51; instantaneous visualizations: (a) unforced supersonic jet with AR=2, (b) axially forced subsonic jet with AR=4
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Contours of streamwise vorticity projected onto the side and bottom walls, vortex lines and iso-surfaces for Q=1 for (a) MILES+WM at 603 resolution at Reτ=2030 and (b) OEEVM+WM at 903 resolution at Reτ=2030
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Time-averaged (or mean) velocity profiles 〈v̄1〉 normalized by the friction velocity uτ versus the wall-normal distance at Reτ=395 (blue), Reτ=2030 (green), and Reτ=10,000 (red) for all channel flow cases reported in Table 1. Panel (a) represents outer scaling whereas panel (b) represents inner scaling.
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First and second-order statistical moments of the streamwise velocity component, 〈v̄〉x and v̄rmsx, respectively. Panels (a) to (c) show 〈v̄〉x at x/h=1.0, 2.0, and 3.0, respectively, whereas panels (d) to (f ) show v̄rmsx at x/h=1.0, 2.0, and 3.0, respectively. Legend: (○) experiments, 86, (–) MILES+WM, ([[dashed_line]]) OEEVM+WM and ([[dot_dash_line]]) OEEVM. Red (darker) lines represent simulations using the top-hat inlet velocity profile, whereas blue (lighter) lines represent simulations using the flattened parabolic inlet velocity profile.



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