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Research Papers: Alternative Energy Sources

Investigation of Flow Over an Airfoil Using a Hybrid Detached Eddy Simulation–Algebraic Stress Turbulence Model

[+] Author and Article Information
Saman Beyhaghi

Department of Mechanical Engineering,
University of Wisconsin-Milwaukee,
3200 N. Cramer Street,
Milwaukee, WI 53211
e-mail: beyhagh2@uwm.edu

Ryoichi S. Amano

Fellow ASME
Department of Mechanical Engineering,
University of Wisconsin-Milwaukee,
3200 N. Cramer Street,
Milwaukee, WI 53211
e-mail: amano@uwm.edu

1Corresponding author.

Contributed by the Advanced Energy Systems Division of ASME for publication in the JOURNAL OF ENERGY RESOURCES TECHNOLOGY. Manuscript received November 1, 2016; final manuscript received February 10, 2017; published online March 16, 2017. Assoc. Editor: Ashwani K. Gupta.

J. Energy Resour. Technol 139(5), 051206 (Mar 16, 2017) (9 pages) Paper No: JERT-16-1436; doi: 10.1115/1.4036050 History: Received November 01, 2016; Revised February 10, 2017

Turbulent air flow over an NACA 4412 airfoil is investigated computationally. To overcome the near-wall inaccuracies of higher order turbulence models such as large Eddy simulation (LES) and detached Eddy simulation (DES), it is proposed to couple DES with algebraic stress model (ASM). Angles of attack (AoA) of 0 and 14 deg are studied for an airfoil subjected to flow with Re = 1.6 × 106. Distribution of the pressure coefficient at airfoil surface and the chordwise velocity component at four locations near the trailing edge are determined. Results of the baseline DES and hybrid DES–ASM models are compared against published data. It is demonstrated that the proposed hybrid model can slightly improve the flow predictions made by the DES model. Findings of this research can be used for the improvement of the near-wall flow predictions for wind turbine applications.

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References

Figures

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Fig. 1

The computational domain and the mesh generated around a NACA 4412 airfoil: (a) geometry, (b) mesh around the airfoil, (c) mesh magnified near the leading edge, and (d) mesh magnified near the trailing edge

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Fig. 2

The airfoil considered for this study: (a) the geometry and (b) distribution of y+ after a converged solution at AoA = 0 deg

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Fig. 3

(a) The four near-trailing-edge lines normal to the airfoil surface, located at normalized chordwise lengths x/c of 0.79, 0.84, 0.89, and 0.95 and (b) airfoil surface midspan where the pressure coefficient data is gathered from

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Fig. 4

Distribution of: (a) the normalized chordwise velocity component and (b) pressure coefficient in the midspan plane, near the airfoil surface, for AoA = 0 deg, and Re = 1.6 × 106

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Fig. 5

Distribution of the pressure coefficient with negative sign at AoA = 0 deg at the midspan of the airfoil surface, determined from different turbulence models and the published experimental data: (a) the entire curve, (b) near the leading-edge, (c) in the midchord, and (d) near the trailing-edge

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Fig. 6

Distribution of: (a) the normalized chordwise velocity component and (b) pressure coefficient in the midspan plane, near the airfoil surface, for AoA = 14 deg, and Re = 1.6 × 106

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Fig. 7

Distribution of the pressure coefficient with negative sign at AoA = 14 deg at the midspan of the airfoil surface, determined from different turbulence models and the published experimental data: (a) the entire curve, (b) near the leading-edge, and (c) near the trailing-edge

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Fig. 8

Velocity profiles for AoA = 14 deg case obtained from two different turbulence models and the experimental data, at four normalized chordwise locations x/c: 0.79, 0.84, 0.89, and 0.95

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Fig. 9

Lift and drag coefficients obtained for the angle of attack of 14 deg from DES and DES–ASM turbulence models and an experimental set of data from the literature

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