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This paper presents a method for constructing flow fields with proper orthogonal decomposition (POD) basis functions or modes with great reduction on the computational cost. Using this approach, it is possible to construct the entire aerodynamic flow fields 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 RAE2822 airfoil in transonic region and varying inflow Mach number to AGARD445.6 wing. The results demonstrate that the POD procedure could provide highly accurate flow fields reconstruction effectively when just a very little amount of data is known. It is a simple, effective method for digit wind tunnel, flow control, and airfoil design.