Numerical study of three-dimensional flow characteristics around the wing airfoil E562 with forward and rearward wingtip fence

Airfoil is an aerodynamic model that is widely used both on aircraft wings, Unmanned Aerial Vehicle (UAV) and fluid machines such as pumps, compressors, and turbines. The airfoil on aircraft wings with the resulting lift force is used to lift the entire aircraft. Therefore, the researchers concentrate more on wing modification so that the resulting lift is more optimal. Increased performance of the airfoil on the wing can be done in various ways, one of which is adding a winglet to reduce drag. It is hoped that a large enough lift and drag ratio will improve aircraft performance. This research was conducted by numerical simulation using Ansys 19.0. with turbulent model k-ω SST. The velocity flow rate used is 10 m / s (Re = 2.3 × 10⁴) with α = 0°, 2°, 4°, 6°, 8°, 10°, 12°, 15°, 16°, 17°, 19° and 20°. The test model is an Eppler 562 (E562) airfoil with and without a winglet. From this study, tip vortex was seen in plain wings, forward wingtip fence and rearward wingtip fence with lower speeds. In the area that has been separated (wake) which is indicated by a lower speed in the three configurations × = 1c. In the z = 1.5c area, it is shown that there is a pathline pattern difference between the three configurations. It is shown that the influence of the three-dimensional flow on the rearward wingtip fence where there is a higher velocity in the upper surface area. In the trailing edge, z = 1.9 shows that there is a pathline from the lower surface to the upper surface in the plain wing and rearward wingtip fence.