Abstract: High-pressure capturing wing (HCW) configuration is a novel aerodynamic design for hypersonic vehicles with large volume, high lift, and high lift-to-drag ratio. Recently, comprehensive studies have shown that HCW can effectively improve the lift force and the lift-to-drag ratio of vehicles in the continuous flow regime, and alleviate the contradiction between high volume and high lift-to-drag ratio in aircraft design. In order to explore the aerodynamic characteristics of HCW in different flow regimes (70~100 km), a geometry of wedge-plate combination is taken as a simplified computational model, and the direct simulation Monte Carlo (DSMC) method is employed to investigate the flow field and wall aerodynamic force/heat characteristics under typical hypersonic conditions (Ma = 20). The simulation results show that as the flight altitude increases, the aircraft-induced shock thickness increases, the shock edge gradually becomes fuzzy, and the pressure interference tends to occur in the open channel between the body and HCW. The friction coefficient of HCW increases rapidly with the increase of rarefaction, which becomes an important factor restricting the lift-to-drag ratio of HCW. Furthermore, the effect of accommodation coefficient on the aerodynamic force/heat of the aircraft increases with the rarefaction degree. Reducing the accommodation coefficient can significantly reduce the shear stress and heat flux of HCW, which is an efficient way to reduce the drag and aerodynamic heating, thus can improve the aerodynamic performance.