This chapter presents the aerodynamic design of four components of an UAV; namely wing, vertical tail, horizontal tail, and fuselage. The primary objective of aerodynamic design is to optimize the UAV outer shape such that the lift is maximized, while the drag and pitching moment are minimized. The chapter provides the UAV aerodynamic design flowchart. In the aerodynamic design of a fixed‐wing UAV and quadcopter, the cost requirements as well as the minimum drag must be simultaneously considered. A well‐designed outer shape can reduce the drag of a UAV as much as 50%. The first step is to identify and list the aerodynamic design requirements. Next, the designer has to design each component (wing, fuselage, tail, body) individually. When the specifications of each component are determined, a systems engineering approach is needed to evaluate the aerodynamic efficiency of the entire vehicle as one body.
Aerodynamic Design
Design of Unmanned Aerial Systems ; 101-140
2020-03-23
40 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Emerald Group Publishing | 1973
Engineering Index Backfile | 1939
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