Abstract: Design of a subsonic axial flow compressor stage has been formulated as a nonlinear multiobjective mathematical programing problem in which minimizing the aerodynamic losses and the weight of the stage,and maximizing the compressor stage stall margin are selected as the objectives.Aerodynamical and mechanical constraints are considered in the problem formulation.A model for estimating the performance of the compressor stage is also presented.Three objective functions,eight design variables and fourty-six constraint conditions are involved in the optimization.A numerical optimization is given for a subsonic axial compressor stage with maximum efficiency,minimum weight,maximum stall margin,in which weighted optimum relationship between efficiency,weight and stall margin has been obtained.