The high-pressure capture wing (HCW) configuration has excellent aerodynamic characteristics verified by theoretical, experimental, and numerical simulation methods. It has a good effect on improving vehicle lift at hypersonic speed. A HCW-V configuration based on the HCW was proposed in this paper. This configuration further increased the vehicle's lift by increasing the wedge angle of the capture wing and forming a compression plane on the lower surface. We obtained the pressure ratio relationship between the upper and lower surfaces of the HCW-V configuration concerning the free-stream airflow Mach number, the body compression angle, and the captive wing wedge angle based on theoretical derivation. It was nearly 60% higher than the HCW configuration pressure ratio. In addition, the influence of the HCW-V configuration on the vehicle's aerodynamic characteristics at different Mach numbers and body compression angles was studied through numerical simulation methods. The HCW-V configuration improved the lift-to-drag ratio by at least 25% compared with the HCW configuration. The expression of the lift coefficient of the vehicle C-L=-0.095Ma(infinity)tan delta +2.352tan delta +0.031 theta +0.010 under the model presented was obtained in this study. Meanwhile, the adaptability of this configuration to varied Mach number and attack angle was investigated further. The average lift-to-drag ratio of HCW-V was increased by 23.7% and 7.09% at varying Mach numbers and angles of attack. The lift-to-drag ratio of the three-dimensional HCW-V configuration is 14% higher than that of the HCW configuration when the wedge angle is 4.19 degrees.
