عنوان مقاله [English]
In this research, the aerodynamic performance of a wing with NASA SC (2) -0714 airfoil and a high-lift configuration, including the main element and the slotted flap at the trailing edge, has been experimentally investigated. Experiments were performed in a wind tunnel at a Reynolds number of 1.01×106 under different angles of attack in the range of -10 to 25° and also flap deflection angles of 0, 20, and 35°. In these experiments, aerodynamic efficiency and wing stall characteristics in different conditions have been determined using force measurements. Also, by measuring the pressure distribution in the middle section of the main element and flap, as well as the total pressure loss in the wake, the onset of the flow separation and the wake profile have been determined, respectively. The results of this study show that by designing the high-lift configuration and using the slotted flap at the trailing edge, the maximum lift coefficient at the flap deflection angle of 35° has increased by 58% compared to the airfoil without high-lift configuration.