In response to the design performance requirements of the small solar-powered aircraft, the overall design and simulation analysis of the aircraft was conducted. Firstly, the overall design parameters of the aircraft was determined based on wing loads, and SD7037 was selected as the reference airfoil. The fluent software was used to optimize the airfoil design based on the NSGA-Ⅱ（non-dominated sorting genetic algorithm Ⅱ). Secondly, the fluent software was used to simulate and analyze the overall aerodynamic characteristics of the aircraft. Thirdly, based on the Workbench method, the aerodynamic force was applied to the surface of the wing through the unidirectional fluid-structure coupling method, and numerical simulation analysis of the total stress and deformation of the wing structure was carried out. Finally, the topology optimization method had been used to optimize the design of the wing rib structure, and the stress, total deformation, and modal values of the optimized wing structure was analyzed again. The research results had shown that the drag coefficient of the optimized wing profile had decreased by about 2.47%, the lift coefficient had increased by about 5.64%, and the lift-to-drag ratio had increased by about 8.31%. The weight of the wing structure had decreased by 26%, the maximum stress had decreased by 11.77%, the maximum total deformation had decreased by 30.81%, and the natural frequencies of the first four modes had all increased.