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.