Design and Aerodynamic Analysis of Fixed-Wing Vertical Take-Off Landing (FW-VTOL) UAV

This study aims to produce a Fixed Wing-Vertical Takeoff Landing (FW-VTOL) design that has good aerodynamic characteristics on its wing and fuselage. The process begins with determining the Design Requirement Objective (DRO). According DRO, aircraft is designed be able operate at speeds of 14 m/s an altitude 120 m (cruise phase) above ground level. Maximum Weight (MTOW) planned estimated using previous research data. Based calculations, for it have flight time 30 minutes, MTOW FW-VTOL 5.2 kg. fuselage were carried out by referring Three candidate airfoils proposed, their determined XFLR5 software. three proposed candidates are also calculated. At angle attack 30, Eppler 66 airfoil produces most lift coefficient lift-to-drag ratio 0.8775 94.152, respectively. While NACA 4412 S9000 create coefficients 0.7963 0.7963, From calculation characteristics, first, second, third drag values 0.1397, 0.1576, 0.1368, then input into decision matrix table. As result, selected 66, while we choose candidate.