Due to actors such as calculation grid resolution, numerical discretization error, and turbulence model adaptability, obvious deviation often exist between CFD predicted pressure data and experimental pressure data. It is thus risky to directly use CFD predicted pressure data to carry out structural strength or aeroelastic analysis. 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, enabling high accuracy and high resolution pressure distribution reconstruction. Firstly, the difference between the pressure distribution data at the test point and the pressure distribution data predicted by CFD is calculated by linear interpolation, and then the difference is decomposed into continuous smooth part and discontinuous part by Laplace fairing method. The continuous smooth part of pressure difference is processed by high-order interpolation, and the discontinuous 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. Results from both test and application show that the delamination pressure data modified method achieves high accuracy, and can obtain more accurate modified results even under the condition of less pressure test measurement points.

The method of selecting partial grid points on the coupling interface to build the interpolation matrix of coupling data is typically used in aeroelastic modeling in order to decrease the interpolation matrix’s scale and increase its efficiency. Now, the selection of the interpolation points from the coupling interface is achieved manually and has issues of high time cost, wrong selection or missing selection when the number of grid points is large. In order to solve the problem caused by manual selection, a two-step automatic selection algorithm of the interpolation points on the coupled interface, which is based on the extraction and reduction of boundary grid points, is presented. Firstly, the adjacent information of grid elements is reconstructed through the node index data of each element in the structural finite element model. The grid points are classified into boundary and interior points with the use of the adjacent information and the boundary grid points are extracted directly. Secondly, the boundary grid points are reduced to create the coupling interface’s interpolation point set using the greedy algorithm and radial basis function (RBF) interpolation, which is frequently used in grid deformation. The grid point with the largest interpolation error is then gradually added to the point set. Finally, the automatic selection algorithm is tested to investigate the influence of parameters through the flying wing case and applied to the static aeroelasticity simulation of AGARD445.6 and DLR-F6 models. The test and simulation data demonstrate that the present algorithm can construct the interpolation point set of the coupling interface automatically and obtain approximate simulation results as manual selection.