ZONAL MODELING OF HYPERSONIC AERODYNAMIC FORCES FOR HIGH-PRESSURE CAPTURING WING CONFIGURATIONS

Shape optimization and efficient aerodynamic prediction are crucial for enhancing the overall performance of high-pressure capturing wing (HCW) configurations. Although existing methods can achieve rapid aerodynamic prediction for specific configurations in hypersonic flows over the capturing wing’s lower surface, challenges remain in determining the baseline shape and modeling the aerodynamic forces of the entire vehicle. The determination of the baseline shape must balance effective coverage of the high-pressure region with proper removal of the low-pressure region, thus necessitating a modeling strategy that can simultaneously handle shape generation and rapid aerodynamic force prediction. To address these issues, this paper proposes a zonal modeling method for hypersonic aerodynamic forces. Based on the pressure distribution on the lower surface, the method first generates a baseline capturing wing shape that effectively captures the high-pressure region while removing the low-pressure region, thereby overcoming the reliance on empirical design. Subsequently, the entire vehicle is decomposed into three zones consisting of the upper surface of the capturing wing, the lower surface, and the body, and zonal modeling is performed using techniques such as surrogate models and the reference temperature method. The total aerodynamic forces are obtained by superimposing the contributions from each zone. Validation against typical configurations shows that, under various geometric parameters and inflow conditions, the predicted lift coefficient of the entire vehicle deviates from computational fluid dynamics (CFD) results by no more than 2.3%, the drag coefficient error is within 4.0%, and the lift-to-drag ratio error is within 5.0%. While enabling accurate prediction of whole-vehicle aerodynamic forces, the proposed method reduces the computational time by approximately three orders of magnitude compared with numerical simulations, thereby providing an effective tool for the engineering optimization of high-pressure capturing wing configurations.