RAPID PREDICTION METHOD FOR HIGH-PRESSURE CAPTURING WING SURFACE FLOW FIELD BASED ON PROPER ORTHOGONAL DECOMPOSITION AND SURROGATE MODEL

The rapid prediction of aerodynamic characteristics for hypersonic vehicles is a critical component in their multidisciplinary optimization design. Currently, engineering calculation methods for hypersonic aerodynamic characteristics have matured and are widely applied to conventional aerodynamic configurations such as lifting bodies and wing-body combinations. These methods are highly efficient and provide reasonably accurate results for traditional designs. However, traditional engineering calculation methods face significant limitations when dealing with novel aerodynamic configurations like high-pressure capturing wing (HCW), where there is substantial aerodynamic interaction between components. This limitation stems from the inability of conventional methods to accurately capture the complex flow interactions and pressure distributions associated with such advanced configurations. To address this issue, this paper proposes an efficient and accurate rapid prediction method for the surface flow field of HCW by integrating computational fluid dynamics (CFD) technology, proper orthogonal decomposition (POD) method, and radial basis function surrogate modeling. Based on this, a comprehensive framework for rapid prediction of aerodynamic characteristics is constructed. Considering the basic design principles of HCW and the influence of key geometric parameters and inflow conditions, the complex pressure distributions on the lower surface of the capturing wing for a typical HCW configuration were predicted and validated. The research results indicate that when 13 POD basis modes are retained, the average relative error in wing surface pressure prediction compared to direct CFD calculation results is only 1.6%, and the aerodynamic force prediction error is as low as 0.3%. It should be noted that further increasing the number of POD basis modes does not significantly enhance prediction accuracy. This method ensures high-accuracy flow field reconstruction and prediction while significantly improving computational efficiency, providing reliable technical support for the design optimization of HCW configurations. The proposed approach has the potential to be extended to other complex aerodynamic configurations with strong interaction effects, thereby contributing to the advancement of hypersonic vehicle design methodologies.