Optimum design of a flexible wing for portable aerial vehicle

In this paper, the aerodynamic characteristics of a flexible wing of low aspect ratio designed for a portable aerial vehicle (PAV) at low Reynolds number are analysed. In the analysis, the aeroelastic effect due to the elastic deformation of the flexible wing on the lift-drag ratio has been taken into account by using a bidirectional fluid-structure loose coupling method. Three types of structural layout for the flexible wing with the primary structure made of carbon/epoxy composite covered by nylon fabric skin are designed and compared. The numerical analysis results show that the flexible wing has improved lift-drag ratio and stall characteristics comparing with a rigid wing. A prototype of the optimised wing model has been manufactured for testing purpose. Based on the work, the wing design and manufacture methods for PAV are discussed according to specific design requirements.