STUDI EKSPERIMEN KARAKTERISTIK AERODINAMIKA PENGARUH TRAPEZOIDAL VORTEX GENERATOR PADA AIRFOIL NACA 43018 DENGAN SMOKE VISUALIZATION

Currently, transportation technology is advancing over time, such as
aircraft transportation technology. Airplanes can fly because of a slightly curved
wing shape or usually called an airfoil. Stall can occur when flow separation occurs
in the flow section (boundary layer) attached to the wing. Flow separation occurs
when the angle of attack begins to increase. This can be done by attempting to add
a turbulent generator to the upper surface of the airfoil. Vortex generator is one
type of turbulent generator that can accelerate the transition from laminar boundary
layer to turbulent boundary layer.
In this research, the topic studied is the characteristics of fluid flow across
a trapezoidal type vortex generator using the smoke visualization method. This
research uses a tool in the form of an open circuit wind tunnel. Which aims to
analyze the effect of a trapezoidal type vortex generator on the fluid flow formed
at the upper surface across the NACA 43018 airfoil with varying vortex generator
position and angle of attack ((α)). Vortex generator with straight arrangement,
vortex generator distance x/c 15% of the leading edge, angle of attack (α) 0°, 4°,
8°, 10°, 15°, and 17°, and freestream velocities used are 3 m/s and 5 m/s.
The results of this study are expected to improve aerodynamic performance
and flow phenomena around the airfoil. The improvement in the aerodynamic
performance of the aircraft from 0° angle of attack to 12° angle of attack is
evidenced by the increase in the transition velocity from laminar boundary layer to
turbulent boundary layer. The resulting turbulent boundary layer flow is useful for
increasing the flow momentum used to resist adverse pressure gradients and delay
separation.
Keywords: Airfoil NACA 43018, Trapezoidal Vortex Generator, Smoke Generator,
Wind Tunnel.