Sparse reconstruction of surface pressure coefficient based on compressed sensing

Wind tunnel test is an important means to obtain aerodynamic loads. However, due to the limited space location and experimental cost, it is usually difficult to arrange enough pressure taps on the complex model surface to obtain complete surface pressure distribution information. Hence, the accuracy of the lift and the pitching moment calculated by the direct integration may fail to meet expectations. This paper presents a sparse fusion method to reconstruct the complete surface pressure distribution based on the limited wind tunnel test data. By integrating the reconstruction resulting surface data over a complete aerodynamic surface, the corresponding aerodynamic coefficients are obtained and are in good agreement with the experimental results. The accuracy of the proposed method is verified by two-dimensional airfoil flow and three-dimensional steady ONER-M6 wing flow examples. The reconstruction results can accurately match the experimental results. The developed reconstruction method largely solves the problem of fine reconstruction of distributed load under the condition of limited space and sparse observation.