EFFECTS OF SWEPT BACK AND TWIST ANGLE ON THE USE OF WING AIRFOIL NACA 20612 TO AERODYNAMIC PERFORMANCE

The use of twist angle on the wing has been used on almost all aircraft wings. The purpose of using this configuration is to delay wingtip stall and even out the lift distribution. The effect of twist angle will be different on different airfoils and wings, especially on the aerodynamic performance of the wing. This research discusses the effect of twist angle on swept back wing compared to rectangular wing or plain wing. This research was conducted because currently the NASA 20612 used on the Embraer 145 aircraft does not use the twist angle. Numerical simulations were carried out with K-ɛ Realizable turbulent model at freestream velocity of 230 m/s. This study shows that the use of twist angle affects the lift to drag ratio where there is a reduction in the total drag coefficient using this design. In addition, the use of twist angle and swept angle in this study reduces the occurrence of induced drag coefficient and delays the occurrence of stall.