Two-Dimensional CFD Analysis of the Aerodynamic Characteristics of an Isolated NACA 2412 Airfoil
DOI:
https://doi.org/10.63746/njtd.v23i3.4028Keywords:
NACA 2412 Airfoil, Computational fluid dynamics, Angles of attack, Lift and drag coefficients, Wind turbine aerodynamicsAbstract
Flow separation and stall point at high angles of attack pose a significant obstacle to the efficiency of wind turbines. This study focuses on analysing the aerodynamic behaviour and determining the optimal operating angle of the NACA2412 isolated Airfoil section. The methodology involved performing time-stabilized two-dimensional Steady-state numerical simulation (2D CFD) using ANSYS Fluent R17.2 software to solve the Navier-Stokes equations in conjunction with the k-? SST turbulence model. A C-grid computational field was constructed around the section with a chord of length 1 m and a maximum thickness of 0.12 m, at a Reynolds number of 6.77 x 105, an inlet flow velocity of 10 m/s, and a turbulence intensity of less than 0.1%. The analysis was conducted across angles of attack ranging from 0° to15° with a 1° step, and the validity of the results was based on network independence studies and reference verification. The digital outputs showed a steady increase in the lift factor up to an angle of 9° in conjunction with a drag factor of 0.04, with the lift-to-drag ratio recording its highest level at 21.07. Exceeding this angle led to an expansion of the separation range of the boundary layer, resulting in aerodynamic stall and a sharp drop in performance. These metrics provide accurate design inputs to reduce dynamic separation and improve turbine efficiency.
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