Aircraft is the science of aerodynamics that is associated with fluid flow, which is related to performance in today's aviation. One of them is technological advances in the world of aviation, namely various developments and modifications of airfoils that are carried out to delay flow separation, one of which is with a vortex generator. The flow separation event in the frictional flow on the surface of the wing (boundary Layer) can cause a stall. Therefore, by delaying the separation, the drag will be small and will get an increase in the lift force. The research study is the characteristic of fluid flow that crosses a parabolic vortex generator with the oil flow visualization method. This study aims to visually observe the fluid flow characteristics on the upper surface crossing the NACA 43018 airfoil with varying positions of the vortex generator and angle of attack (AoA). The vortex generator profile is positioned x/c = 20% from the leading edge. By using variations of Reynolds Number (Re) and angle of attack (α) on the airfoil. The freestream speed used is 20 m/s, at angles of attack (α) = 0°, 4°, 10°, 12°, 15°, and 17°. It can be proven that this research with the addition of a parabolic vortex generator increases the aerodynamic performance of the airfoil, where the aircraft from AoA 0°to 12°proves that the increasing speed of the transition to the laminar boundary layer is concluded to be a turbulent boundary layer. Based on visual experiments using a parabolic vortex generator, it shows that there is a delay in flow separation on the upper surface of NACA 43018 at an angle of attack of α = 12°to 15°.

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.

In this study, the topic studied was the characteristics of airflow passing through the gothic-type generator vortex by the smoke generator method. The purpose of this study was to visually observe the characteristics of the airflow on the upper surface passing through the NACA 43018 airfoil with varying angle of attack positions. The vortex profile of the generator x/c = 20% of the leading edge. Variations in this study are the angle of attack (α) and the placement of the generator vortex on the airfoil. The freestream speed used is a speed of 5 m/s, and at an angle of attack (α) of 0°, 3°, 6°, 9°, 12°, and 15°. From this study, it was found that the ratio of separation points between airfoils without VG compared to airfoils with VG and D = 10 mm at angles of attack (α) = 0°, 3°, 6°, 9°, 12°, and 15°had significant differences in separation points. Airfoil with VG and D = 20 mm at an angle of attack (α) = 0°, 3°, 6°, 9°, 12°, and 15°can delay separation better than D = 10 mm.

The development of science and technology affects all sectors of life, one of them is technological progress in the aviation world. The wing is the most important part of an aircraft because the wing produces an elevator When moving against the airflow because of its airfoil shape. The airfoils found on the aircraft have a pressure difference between the upper surface and the lower surface which causes the aircraft to get lifted. To improve the performance of the airfoil, the wing is added to the wing of the generator vortex. The method used in this study used a wind tunnel. By using smoke in the wind tunnel and fan acceleration against smoke. As well as changing some angles and distances of the gothic vortex generator (VG). Using Eppler 562 with a freestream velocity has a speed of 5 m/s and an angle of attack α = 0°, 4°, 10°, 16°, 20°, and variations in the spacing between gothic vortex generators (VG). The result obtained from this study is the appearance of airflow performance around the airfoil. This is because there is a difference between airfoils that use a gothic vortex generator and do not use a gothic vortex generator. Airfoils that use gothic vortex generators have simpler partition points than airfoils that do not use gothic vortex generators.

At this time, it has become commonplace for aircraft to use high lift devices. The high lift devices used include flaps, slats, slots, elevators, ailerons, and others. This study examines the effect of multiple elements on the wing, especially the combination of slat slots and flaps in several configurations.. This research was conducted with numerical simulations on wing airfoil NACA 43018. The observed conditions were rectangular wing (no slats, slots, and flaps) compared to the use of slats, slots, and flaps under steady flight conditions. The angles of attack used are (α) = 0o, 2o, 4o, 6o, 8o, 10o,12o,15o, 16o,17o,19o, and 20o. Numerical simulation using Ansys 19.1 application with turbulent model k-ε realizable. The use of slats, slots, and flaps does not result in a shift in the stall point but tends to increase aerodynamic performance (CL/CD)which is very significant. By paying attention to pressure drag, viscous drag and the resulting induced drag, the use of slats, slots, and flaps reduces a large amount of induced drag so that the lift to drag ratio increases.