In order to research the impact of blade deflection on aerodynamic performance of a transonic fan

a numeric program was developed to simulate the deflection of fan blades under aerodynamic loads with fluid-structural interaction method.The aerodynamic model of the fluid flow was based on solving the unsteady three-dimensional(3-D) compressible Reynolds averaged Navier-Stokes equation.The blade vibration was predicted with a linear aeroelasticity model by solving the structure dynamic equation simultaneously with aerodynamic equations.The blade deformation under unsteady aerodynamic loads of the NASA(National Aeronautics and Space Administration) Rotor 67 blade was computed

and the impact on the flowfield and aerodynamic performance was analyzed.