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Stall and Pos-Stall of airfoils for small wind turbines: Numerical and Experimental Analysis Antonio G. Lopes1, Jorge A. V. Alé2, Almerindo D. Ferreira1, Gabriel da S. Simioni2, Vinicius K. Calgaro2 1 Department of Mechanical Engineering, University of Coimbra, Coimbra, Portugal 2 CE-EOLICA Wind Energy Center, Pontifícia Universidade Católica do Rio Grande do Sul, Porto Alegre, Brazil email: antonio.gameiro@dem.uc.pt, villar@pucrs.br , almerindo.ferreira@dem.uc.pt, simioni@pucrs.br.
ABSTRACT: Experimental and numerical results are presented for the aerodynamic coefficients of the NACA 0012 and NACA 0018 airfoils. Numerical tests include different turbulence models and advection schemes, using three software packages: EasyCFD_G, OpenFOAM and ANSYS Fluent. The obtained CFD simulations show that predictions of the aerodynamic coefficients agree very well with experimental data at low angles of attack. Limitations of the simulations are shown for airfoils operating at high angles of attack. An interesting bifurcation phenomenon was detected in the near post-stall region, with two numerical solutions for the flow: a steady and an unsteady solution. In the post-stall region, both drag and lift are overestimated for unsteady solutions. KEY WORDS: Airfoils; Small Wind Turbines; CFD; Wind Tunnel Data. 1
INTRODUCTION
Wind turbines rotor blades are designed to optimize the energy captured from the wind. Most computer codes used to determine the aerodynamic performance of wind turbines are based on the blade element theory (BEM), which requires data of airfoils lift (CL) and drag (CD) coefficients. When blades operate at low angles of attack, numerical simulation is able to correctly reproduce experimental CL and CD values. However, when the angle of attack reaches, or exceeds, the stall angle, there is a wide divergence of computational results when compared with experimental results. Moreover, the vast majority of experimental data pertains conditions of interest for aviation industry, namely high Reynolds number and low angles of attack. Efforts have been made by the wind industry to overcome these shortcomings, providing available data specific to wind rotors airfoils. Yet there are other limitations when working with wind turbine airfoils. The rotor blades of large turbines can operate in the Reynolds range of 2×106 to 6×106. However, small wind turbines operate in the Reynolds range of 5×104 to 5×105. In both cases, the available information is still limited to experimental results mostly in post stall region. These challenges have motivated the use of CFD models using the RANS equations to predict the aerodynamic coefficients of airfoils for wind turbines. Despite several efforts, there is a wide divergence of results mainly in the post stall. This paper aims to contribute to this research, presenting CFD results for the flow around the NACA 0012 and NACA 0018, obtained with EasyCFD_G [1] software, with OpenFOAM [2] and with ANSYS Fluent [3] software and comparing with experimental data. 2
THEORETICAL BACKGROUND
2.1
Basic transport equations
For present simulations, the Navier-Stokes equations are considered using a transient 2D form:
∂ ( ρu )
+
r ∂ ∂ ∂ ∂ ∂u 2 ρu2 + ( ρ uw ) = Γ 2 − divV + Γ ∂x ∂z ∂x ∂x 3 ∂ z
∂ ( ρ w)
+
∂ ∂ ∂ ( ρuw) + ρ w2 = Γ ∂x ∂z ∂z
∂t
∂t
(
)
(
)
r ∂ ∂w 2 2 ∂ z − 3 divV + ∂ x Γ
∂ u ∂ w ∂ p ∂ z + ∂ x − ∂ x
∂ u ∂ w ∂ p ∂ z + ∂ x − ∂ z
(1)
(2)
where p is pressure and Γ is the total viscosity, which includes the contributions of the dynamic and turbulent components Γ , i.e. Γ = µ + µt . The three unknowns u, w, and p in these equations need the mass conservation equation to close the problem:
14th International Conference on Wind Engineering – Porto Alegre, Brazil – June 21-26, 2015