Abstract: A computer program SAFDOP of optimum design by intuitive optimality criteria is introduced for a lifting-surface structure with multiple constraints.The program is capable of performing interdisciplinary analysis,optimum and synthetic optimum designs for stress,deflection,flutter and aeroelastic constraints.Alternate constraint method is adopted for the synthetic optimum design.Excepting that the full stress design is employed for the stress constraint,the uniform derivative criteria are used for the other constraints.For practical purpose,the element linking weight is considered as an independent design variable,and the design variables with derivative smaller than the target derivative or even being negative are eliminated by self-sieve method from the computation in the optimum design,by considering the automated generation of some initial numerical data.The program has been applied to a typical fighter wing structure and proved to be feasible.