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Research Papers: Fundamental Issues and Canonical Flows

A Scale-Adaptive Turbulence Model Based on the k-Equation and Recalibrated Reynolds Stress Constitutive Relation

[+] Author and Article Information
Yang Zhang

School of Aeronautics,
Northwestern Polytechnical University,
Xi'an, Shaanxi 710072, China
e-mail: vvip@nwpu.edu.cn

Jun-Qiang Bai

Professor
School of Aeronautics,
Northwestern Polytechnical University,
Xi'an, Shaanxi 710072, China
e-mail: junqiang@nwpu.edu.cn

Jing-Lei Xu

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China
e-mail: xujl@buaa.edu.cn

1Corresponding author.

Manuscript received March 5, 2015; final manuscript received December 27, 2015; published online March 24, 2016. Assoc. Editor: Sharath S. Girimaji.

J. Fluids Eng 138(6), 061203 (Mar 24, 2016) (11 pages) Paper No: FE-15-1141; doi: 10.1115/1.4032535 History: Received March 05, 2015; Revised December 27, 2015

An algebraic relationship between turbulent dissipation rate and von Karman length are used to dismiss the transport equation of turbulent dissipation rate in standard kε (SKE) turbulence model. Meanwhile, a recalibrated Bradshaw's assumption is built based on the data from a boundary layer flow of turbulent flat plate simulated by direct numerical simulation (DNS). The JL model is reformed to a one-equation model which only depends on the turbulent energy, so the new model can also be called kinetic-energy dependent only (KDO) turbulence model. As the KDO model is using the von Karman length scale, it can automatically adjust to fit the resolved structures of the local flow. Results will be shown for the boundary layer flow on a turbulent flat plate, and the external flows of an NACA4412 airfoil, an ONERA-M6 wing, a three dimension delta wing, and an NACA0012 airfoil at deep stall.

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References

Figures

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Fig. 1

a1 plotted against Rey

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Fig. 2

fdyn plotted against y+ and Rey

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Fig. 3

Comparison of velocity profile of the different size meshes at (left) x=0.24 m and (right) x=0.50 m

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Fig. 4

Comparison of skin friction coefficient

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Fig. 5

Comparison of velocity profile at (left) x=0.24 m and (right) x=0.50 m

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Fig. 6

Wall-pressure coefficient for NACA4412

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Fig. 7

Velocity profiles of different locations for NACA4412

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Fig. 8

Turbulence shear-stress of different locations on the upper surface for NACA4412

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Fig. 9

Wall-pressure coefficient at the selected six locations

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Fig. 10

The geometric description of VFE-2 wind tunnel model

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Fig. 11

Wall-pressure coefficient at the six slices

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Fig. 12

Comparison of computed wall-pressure coefficient contour and experimental data

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Fig. 13

Time-history for Cl and Cd

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Fig. 14

Time-averaged wall-pressure coefficient

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Fig. 15

Vortex structures: snapshot of Q-isosurface colored with U/U∞

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