Abstract: High-pressure capturing wing configurations (HCW) are a family of new concepts which are proposed to meet the design requirements of high volumetric efficiency, high lift coefficient, and high lift-to-drag ratio for hypersonic flight vehicles. In order to investigate the flow characteristics as well as the aerodynamic performance of a typical HCW configuration in a wide-speed range, a preliminary study was conducted in this paper. A cone-truncated cone combination geometry is taken as the simplified computational model. Afterwards, a computational fluid dynamics study was carried out under the freestream flow condition of Mach number 0.92 and 0° angle of attack. Besides, a comparison study was conducted on the basis of the results between the configurations with and without the HCW. Numerical results show that there exists a strong aerodynamic interference between the body and the HCW in the transonic flow regime. The results demonstrated that the area of the flow separation section near the tail part increases significantly as a result of appending the HCW. In the opening channel between the fuselage and the HCW, a shock train appears clearly along the flow direction. This phenomenon leads to that the wall pressure on the lower surface of the HCW presents a significant oscillation. Furthermore, the most obvious oscillation appears in the region near the symmetrical plane, and then it gradually fades with the increase of the spanwise distance.