Numerical study of three-dimensional flow characteristics around swept-back angle 0°, 15°, and 30° on wing airfoil Eppler 562.

Airfoil is an aerodynamic structure that is widely used in aircraft wings, UAVs, and fluid engines such as pumps, compressors, and turbines. The airfoil on the UAV wing is used to lift the UAV body where the pressure difference between the top and bottom of the airfoil causes the UAV to get a lift. Improving airfoil performance can be done in various ways, one of which is changing the angle of inclination in the airfoil range (swept angle). This is often seen in almost all types of commercial aircraft such as the Boeing 777 and Airbus 380. The method used in this study is a three-dimensional numerical simulation using Ansys 19.1 software. The specimens were Eppler 562 airfoil with a chord length of 200 mm, aspect ratio (AR) of 5, angle of attack 0°, 2°, 4°, 6°, 8°, 10°,12°,15°, 16°,17°,19°, and 20°. The variation of the swept-back used is angle Λ=0° (unswept), 15°, and 30°. Fluid flow is flowing air with the Reynolds number (Re)=2.34 × 104 in unsteady conditions. From this research, it was found that the variation of the swept-back will change the direction of flow to the wingtip and away from the wing root. This change in flow direction will reduce the occurrence of a vortex-shaped streamline that occurs on the unswept or rectangular wing. However, the variation of the swept-back will increase the tip vortex. [ABSTRACT FROM AUTHOR]