Due to the influence of calculation grid resolution, numerical discretization error, turbulence model adaptability and other factors, there will be obvious deviation between CFD predicted pressure data and experimental pressure data, so it is risky to directly use CFD predicted pressure data to carry out structural strength or aeroelastic analysis. In or-der to solve the problem of insufficient precision and large error of traditional single interpolation method when dealing with the pressure coefficient modified of discontinuous changes of suction peak and shock wave position, this paper develops a method for correcting airfoil CFD pressure data based on hierarchical interpolation, which is used to obtain airfoil pressure distribution data with high accuracy and high resolution. Firstly, the difference between the pressure distribution data at the test point and the pressure distribution data predicted by CFD is calculated by linear interpola-tion, and then the difference is decomposed into continuous smooth part and discontinuous part by Laplace smoothing method. The continuous smooth part of pressure difference is processed by high-order interpolation, and the discon-tinuous smooth part is processed by linear interpolation. If there is still warpage in the pressure data near the shock wave position after interpolation,the warped part will be smoothed by shock position detection and local position linear interpolation. The method is tested using the RAE2822 airfoil test and CFD computed pressure data, and applied to the DLR-F6 wing-body assembly and HIRENASD wing computed pressure coefficient modified. The results of test and application show that the delamination pressure data modified method has good accuracy, and can obtain more accurate modified results even under the condition of less pressure test measurement points.
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