Unmanned Aerial Vehicle structural design

Abstract

This study focuses on the design, analysis, and selection of an airfoil for a heavylifting unmanned aerial vehicle (UAV) with the aim of achieving optimal aerodynamic performance. The UAV is intended for civilian and reconnaissance applications and must be capable of carrying a maximum take-off weight of 450 kg while operating at an altitude of 4000 meters. As such, the airfoil design must provide high lift-to-drag ratios and fulfill specific performance criteria to ensure efficient and reliable operation under the designated conditions.