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TECHNICAL PAPERS

Assessment and Modification of One-Equation Models of Turbulence for Wall-Bounded Flows

[+] Author and Article Information
M. Elkhoury

Department of Mechanical Engineering, Lebanese American University, P. O. Box 36, Byblos, Lebanonmkhoury@lau.edu.lb

J. Fluids Eng 129(7), 921-928 (Jan 25, 2007) (8 pages) doi:10.1115/1.2743666 History: Received September 19, 2006; Revised January 25, 2007

This work assesses the performance of two single-equation eddy viscosity transport models that are based on Menter’s transformation of the k-ε and the k-ω closures. The coefficients of both models are set exactly the same and follow directly from the constants of the standard k-ε closure. This in turn allows a cross-comparison of the effect of two different destruction terms on the performance of single-equation closures. Furthermore, some wall-free modifications to production and destruction terms are proposed and applied to both models. An assessment of the baseline models with and without the proposed modifications against experiments, and the Spalart-Allmaras turbulence model is provided via several boundary-layer computations. Better performance is indicated with the proposed modifications in wall-bounded nonequilibrium flows.

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Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

Analytical law-of-the-wall profile for the flat plate case

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Figure 2

Skin friction profile for the flat plate case

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Figure 3

Mean velocity profiles for NACA 4412 airfoil at x∕c=0.675, 0.731, 0.786, 0.842, 0.897, and 0.953 on the suction surface of airfoil

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Figure 4

Surface pressure distribution over the NACA 0012 airfoil

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Figure 5

Surface pressure distribution over the RAE 2822 Case 10 airfoil

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Figure 6

Surface skin friction distribution over the upper surface of the RAE 2822 Case 10 airfoil

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Figure 7

Surface skin friction coefficient distribution for the Aerospatiale-A airfoil

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Figure 8

Mean streamwise velocity profiles for the Aerospatiale-A airfoil at x∕c=0.3, 0.7, 0.87, 0.96, and 0.99 on the suction side of the airfoil

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Figure 9

Mean velocity profiles for a 45deg slanted backstep at x∕H=1, and 2

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Figure 10

Mean velocity profiles for a 45deg slanted backstep at x∕H=8, and 15

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