Comparative Study on the Aerodynamic Performance of NACA 4412 Airfoil with and Without Slot

Aircraft stalling and spinning are major causes of aviation accidents and fatalities; hence, using slots in airfoils is essential for lowering that risk. There has not been much research on the geometrical dependence of flow features around an airfoil, despite previous studies concentrating on fixed-wing slots. Applications in aircraft wings, wind turbine blades, watercraft, and unmanned aerial vehicles (UAV) demand an understanding of how slots affect airfoils. Using a NACA 4412 airfoil, which is frequently used in the aerospace industry for small-scale transonic flight, this study attempts to examine the effects of a rectangular slot close to the trailing edge. The airfoils with and without slots are compared, taking into account an inflow Mach number of 0.9 and an angle of attack of 0°, 10°, and 16°, respectively. This gives a thorough grasp of the performance characteristics of the airfoil at various angles of attack. The flow around the airfoil was simulated using ANSYS Fluent, a pressure-based solver, and the SST k-omega turbulence model. The production of vortices and their movement towardthe upper surface of the airfoil, followed by the movement of high-pressure air from the lower surface of the airfoil, can be caused by a slot close to the trailing edge. The aerodynamic effectiveness and stability of the airfoil can be considerably impacted by these vortices. The results show that the slot delays flow separation, resulting in a decrease in drag and an increase in lift, particularly at higher angles of attack. Additionally, as the span lengthens, the airfoil's stability grows. The vortices created by the slot can create attached flow and lessen drag by lowering turbulence close to the airfoil's wake. The study emphasizes the solver's aptitude for resolving pressure waves, vortices, and other flow characteristics within and around the airfoil.