The drag characteristics of a wing greatly affect the aerodynamic performance of the aircraft as a whole. This is because the aircraft movement process is controlled by the wing. The use of different airfoils and wing planforms will produce different drag characteristics. The numerical simulation in this study uses the NASA 20612 airfoil used on the Embraer 145 aircraft with three forms of planform wing, namely rectangular, delta, and swept back wing. The turbulent model used is k–ε Realizable with Re = 2.88 × 107. In the rectangular wing, the vorticity is centered on the area behind the wingtip while the delta and swept back wing are partially centered on the area behind the midspan. This shows that the wing planform greatly affects the formation of vorticity which in turn affects the induced drag formed. In the rectangular wing, the separation occurs early in the midspan area while in the delta and swept back wing it is closer to the wingtip area. At the wingtip, delta, and swept-back wings have less tip vortex effect than rectangular wings. This shows that the use of delta and swept-back wings can reduce the occurrence of induced drag on the wing airfoil NACA 20612.