Aerodynamic Performance of Swayasa Aircraft Wing Model against the Effect of Airfoil Flap Angle Configuration

This research aims to determine the aerodynamic performance of the swayasa aircraft airfoil flap angle configuration. The aerodynamic performance is the pressure coefficient (CP) and flow separation of the optimal swayasa aircraft airfoil flap angle configuration. For this purpose, a computational approach using a Computational Fluid Dynamics (CFD) program and experimental research in a sub-sonic wind tunnel were conducted. The wing model of the swayasa aircraft uses the NACA 23012 airfoil model with pressure taps around the surface by giving the same main flap angle (Fu) configuration treatment at 4 levels of flap angle, namely −10°, 0°, 15°and 30°; then each level is given a variation of the control flap or aileron angle (Fk) at angles of −10°, 0°, 15°, 30°, and 45°. Furthermore, an airflow velocity of 22 m/s or Reynolds number (Re) 270,886 was applied at angles of attacks (α) of −10°, 0°, 15°, and 20°. Experimental results show the characteristics of pressure coefficient (CP) and flow separation at the same angle α, forming the same pattern at various angles Fu and angle Fk. Furthermore, the computational results of velocity contours show the configuration of using Fu with Fk, resulting in an increase in pressure on the lower surface of the airfoil at positive Fu angles and a decrease in pressure on the upper surface of the airfoil, resulting in higher vortices or turbulence in the area behind Fu and around Fk.