Abstract：A method for reconstructing flow fields that using proper orthogonal decomposition (POD) basis functions or modes with great reduction on the computational cost is presented. Using this approach, it is possible to construct entire aerodynamic fl ow fi elds from the knowledge of computed aerodynamic data or measured flow data specified on the aerodynamic surfaces, demonstrating a way to effectively combine experimental and computational data. There are three cases here, varying inflow Mach number to NACA0012 airfoil in subsonic region and RAE2822 airfoil in transonic region. The results demonstrate that the POD procedure could provides effectively high accurate fl ow fi elds reconstruction when just very little amount of data is known. It is a simple, effective method for digit wind tunnel, fl ow control, and airfoil design.
2011, 
