Analysis Influence of Trailing Edge Modification on Aerodynamic Performance of Airfoils for Wind Turbine

Shang Ke Yuan; Ren Nian Li

doi:10.4028/www.scientific.net/AMM.220-223.900

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 220-223Analysis Influence of Trailing Edge Modification...

Analysis Influence of Trailing Edge Modification on Aerodynamic Performance of Airfoils for Wind Turbine

Abstract:

The airfoil NACA 4412 commonly employed in wind turbines is modified by attaching a Gurney flap with length of 2% chord at its trailing edge and its remodeled form as well. The SIMPLE algorithm of finite volume method and software FLUENT are respectively used to carry out numerical computation of aerodynamic performances of above-mentioned three airfoils (including the un-modified one), so that their aerodynamic characteristics, pressure distribution on their surface, and streamline around them are obtained for different angles of attack. It is shown by the computation result that the modified airfoils will result in such a strong downwash effect that the pressure distribution on airfoil surface is remarkably altered, the lift coefficient and as well as the slope of lift-drag characteristic curve are increased, and meantime the airfoil stalling is greatly postponed.

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Periodical:

Applied Mechanics and Materials (Volumes 220-223)

Pages:

900-904

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.220-223.900

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Online since:

November 2012

Authors:

Shang Ke Yuan, Ren Nian Li

Keywords:

Aerodynamic Performance, Airfoil, Gurney Flap, Numerical Computation

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