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.