Numerical simulation of the effect of relative thickness on aerodynamic performance improvement of asymmetrical blunt trailing-edge modification

摘要: Abstract In this paper, the aerodynamic performance of wind turbine airfoils with different relative thicknesses and their modifications has been numerically investigated to facilitate a greater understanding effects maximum thickness its position on improvement asymmetrical blunt trailing-edge modification. The lift drag coefficients airfoil NACA4415 are calculated k-ω SST turbulence model, compared experimental data validate simulation accuracy Computational Fluid Dynamics (CFD) approach. modified be by means software Xfoil. best distribution ratio is obtained comparing ratios. original being 1:3 analyze increments lift-drag ratio. Results indicate that increasing thickness, coefficient increment NACA4418 smallest for angle attack more than 9°, as whole decreases first then increases, but average NACA4412 largest, closely followed airfoil. It also showed close leading-edge, decrease increase certain value, respectively, positive larger those NACA4415-mod25 NACA4415-mod20 airfoils. Therefore, medium whose away from leading-edge suited