The reflex airfoils are usually used on the flying-wing electric-powered mini-UAVs to provide longitudinal stability. This deteriorates the performance of the flying wing UAVs, since the maximum lift coefficient and the lift to drag ratio of the reflex airfoils is relatively poor. In order to solve this problem, the flying-wing mini-UAV based on cambered airfoil is studied. In this paper, the structure, motor, weight and battery models are presented. Longitudinal trimmed drag is reduced by the swept wing, geometrical twist as well as optimized dimension of flap and elevon. The CMARC is incorporated into the optimization procedure to compute the aerodynamics and longitudinal stability parameters. Then, the configuration parameters are optimized using the genetic algorithm to maximize the endurance. In comparison with the flying wing mini-UAVs with reflex airfoil, the endurance of the flying wing UAVs with cambered airfoil is increased by 20%. Finally, the effects of the power system efficiency, angle of climb and the size of the battery are analyzed.
