Abstract: According to the given configuration and dimension of composite wing model, the multilevel optimization method was used to determine the design scheme of wing. First, the efficiency evaluation of single factor and comprehensive efficiency evaluation of grey correlation degree were introduced to obtain the optimum wing layout. Then, the structure detail optimization of I-beam wing based on the finite element method and ply design were carried out. Finally, four kinds of typical composite wing models (i.e. skin-foam structure, skin-stiffened structure, front C-beam structure and I-beam structure) were manufactured by using integral forming process based on the method of vacuum bag. Then the three point bending test was used to verify the optimization design. The optimization results show that the I-beam wing has the highest structural efficiency, then followed by the back C-beam wing. The skin-web wing performs with the least structural efficiency. The flange can gain approximate equal strength beam by using constant thickness and variable width. The effectiveness of the optimization method was verified by the experimental results.