Abstract: A method for flow field inverse design is introduced. Using the POD methodology, it is possible to construct entire aerodynamic flow fields from the knowledge of computed aerodynamic flow data or measured flow data specified on the aerodynamic surface. First, the snapshots are obtained to form the POD kernel, and then Singular Values Decomposition (SVD) is used to get POD modes, finally the entire flow field is designed by the POD based the inversed design methodology. Two cases are evaluated for flow field construction validation: (1) subsonic flow around RAE 2822 airfoil; (2) transonic flow around NACA 0012 airfoil. The results in case (1) suggest the method work efficiently not only for interpolation but also for extrapolation problems. The results in case (2) demonstrate that the method reconstructs the entire flow field accurately in transonic flow, in which shock wave presents.