Effect of Using Triangular Vortex Generator Straight Arrangement in Air Naca 43018 with Smoke Generator

Abstract

Airplanes can fly because of the slightly curved wing shape or usually called an airfoil. The occurrence of flow separation on the part of the flow attached to the wing (boundary layer) can cause a stall. Separation of flow occurs when the angle of attack begins to increase. This can be done by adding a turbulent generator to the upper surface airfoil. A vortex generator is a type of turbulent generator that can accelerate the transition from the laminar boundary layer to the turbulent boundary layer. The method uses a tool in the form of a Wind Tunnel Open circuit. By applying smoke to the Wind Tunnel and accelerating the fan against smoke. In this experiment, the variations used are Airfoil NACA 43018, triangular type vortex generator with the straight arrangement, vortex generator distance x/c 20% from the leading edge, angle of attack (α) = 0°, 3°, 6°, 9°, 12°, and 15°, and freestream velocity speed 3 m/s. From the experimental results, this study shows that using a triangular vortex generator has been shown to improve aerodynamic performance and the performance of the NACA 43018 type airfoil. The 43018 type airfoil that uses a vortex generator compared to an airfoil that does not use a vortex generator can increase the transition from laminar flow to turbulent flow.