A global aerodynamic optimization method was proposed for three-dimensional cascade design.The method was applied to the NASA Rotor 37

which was a test transonic compressor cascade representing complex three-dimensional viscous flow structures.The capability of the computational fluid dynamics(CFD) code was validated by comparing the computed results with experimental data available in the open literature.The transonic cascade was optimized for the maximization of the isentropic efficiency under given flow conditions

using constraints on the mass flow rate and the total pressure ratio.The isentropic efficiency of the optimized design was 1.66% higher than that of the reference design

showing a better aerodynamic performance and better off-design performance.It shows that the shock losses of the transonic cascade could be reduced by optimizing the profiles of the transonic cascade and its radial stacking mode.