Análise experimental do escoamento ao redor de um aerofólio convencional com o bordo de fuga serrilhado a baixo reynolds

Abstract

The present work has as main objective the experimental analysis of the air flow around a conventional airfoil (NACA0012) at low Reynolds, and to evaluate the influence on the performance of the airfoil with the serrated trailing edge, in order to understand and determine its aerodynamics characteristics for possible applications in wind generators. The airfoil models were built using CATIAV5® and manufactured using a 3D printer. A small Wind Tunnel and accessory instrumentation were used to carry out the experiments, using a three-component aerodynamic balance, and visualization using the wool tufts technique, showing flow characteristics over the baseline airfoil and with the serrated trailing edge. Initially measurements of lift, drag and moment were determined, with a variation of the angle of attack from 0° to 16° for the Reynolds around 2 x 10^5. Finally, a comparison was made of the results obtained for the two airfoil models, with the curves generated in the XFLR5 given the Reynolds obtained and the coordinates of the NACA 0012 profile, as well as with experimental data from other studies. However, in the case of a 2D profile, it was identified that the flow did not behave in a completely two-dimensional way, therefore, adjustments and future works are recommended.