A viscous inverse problem method used in turbomachinery blade aerodynamic design was presented. The proposed method could be used to directly solve the blade geometry according to the given objective surface pressure distribution or pressure difference distribution from pressure side to suction side. In the proposed method

the blade surface was considered as movable wall

and the movement of the blade wall was evaluated on the basis of the solution of the momentum equation along the normal direction of blade wall. Result shows that

the proposed method is quite robust and needs less computational resources because it is based on the steady RANS(Reynolds-averaged Navier-stokes) simulation

and it does not need viscous correction since the simulation itself is in the real viscous flow environment. Examples using the developed inverse problem method were presented. Verification results show that the proposed method can achieve the desired target in both single blade row and multi-blade row environment

and computational process has good stability and convergence.