Design and CFD Analysis of A Low-Altitude VTOL UAV

Abstract

In this study, in order to develop a vertical takeoff and landing modular body platform that meets takeoff and speed performance, each mission file was prepared for conventional takeoff (CTOL) and vertical takeoff and landing (VTOL) based on the design requirements. The conceptual design took the basic shape and, in the first place, estimated the initial weight of the aircraft components and the entire BOM. After reflecting the components and weights applied to the drones in the design, the main wing shape design, weight center and neutral point prediction, and thrust system design were performed using XFLR5. ANSYS Workbench V14.5 was used for CFD analysis of the aircraft and ICEM-CFD was used as a program to generate Hybrid Mesh (Hexa Mesh & Prism Mesh). Through analytical techniques, the airfoil used for the main wing was designed as NACA4412 and the tail wing was designed as the V-Tail type, which minimizes the aft effects of the thrust device, and the basic airfoil of the tail wing for stability was selected as NACA0009. Because the droneapplied in this study must have the ability to make both a vertical takeoff and a horizontal flight, the N. P. position designed in flight mode and the distance of each rotor of the quadrotor are similarly designed.