Аннотация
This work gives a better understanding of the aerodynamic interference between propeller and wing during different flight phases of a vertical take-off and landing (VSTOL) unmanned aerial vehicle (UAV). A finite-volume solver coupled with a blade element momentum (BEM) theory propeller model, are used to investigate the flow over different wing configurations. The findings contribute to design aspects of a three-rotor fixed-wing UAV capable of VSTOL and loitering. For example, the optimum minimum width of the deflected part of the wing is established. Also the optimum distance of the propeller ahead of the wing is obtained. The main originality is in the novel design of the UAV, which is a hybrid between a fixed-wing and a copter UAV. One of the outcomes of this research is a better understanding of the minimum thrust needed for operation, so keeping energy requirements as low as possible.