Effect of Vortex Generators on NACA2412 Aerofoil at Different Angles of Attack for Aircraft Wings

Vortex generator and aerofoil geometry of the blade enhance the aerodynamic effectiveness of an aircraft wing. In this research work, a wind tunnel experiment was conducted to explore the impact of vortex generators on the aerodynamic characteristics of the NACA2412 airfoil. The primary goal of this study was to analyse the coefficients of lift, drag and CL/CD distributions across the NACA2412 airfoil blade at freestream velocities of 15m/s, 25m/s and 35m/s, utilizing a low-speed subsonic wind tunnel. In the wind tunnel, the impact of NACA2412 profile airfoils has been examined with the help of three component force balance instruments at various angles of attack such as 0, 4, 8, 12 and 16 deg respectively and similarly in negative angle of attack of 0, -4, -8, -12 and -16 deg. The target of the task is to find out the lift coefficient and drag coefficient at different vortex generator such as triangular vortex generator, gothic vortex generator and rectangular vortex generator and their different combination arranged over the wing of NACA2412 aerofoil at x/c of 0.25, 0.5 and 0.75. The results of the study showed that significant variations in the coefficients of lift, drag and CL/CD distributions across the airfoil blade at different freestream velocities and angles of attack.