Abstract: High-pressure capturing wing (HCW) novel aerodynamic layout has good aerodynamic performance in the hypersonic design state, and the import of the new lift wing provides more lift for it under subsonic conditions, but its aerodynamic stability characteristics at subsonic speed have yet to be studied further. In this paper, a parametric HCW concept configuration was presented based on the basic design principle of HCW aerodynamic layout, by adding an HCW with single support to a delta wing-body combination. The influence of wing dihedral/anhedral angle variations on subsonic aerodynamic characteristics of HCW configuration at the angle of attack (AOA) range of 0° to 10° was studied by utilizing uniform experimental design, computational fluid dynamics numerical simulation, and Kriging surrogate model, which regarded the dihedral/anhedral angles of both HCW and delta wing as the design variables. Specifically, the variation law of lift-drag characteristics, longitudinal and lateral-directional stability characteristics, and flow field vortex structures were analyzed. The results show that the influence of wing dihedral/anhedral angles on the lift-drag ratio (L/D) at low AOA is more significant than that at high AOA. The increase in HCW dihedral angle improves L/D of configuration, while the increase in HCW anhedral angle or delta wing dihedral angle reduces L/D. As the delta wing anhedral is increased from 0°, L/D has a slight improvement initially and then slowly reduces. The longitudinal stability, which is generally less affected by wing dihedral/anhedral angles, slightly improves as the HCW dihedral angle increases but reduces as the delta wing dihedral angle increases. Moreover, the lateral stability improves as the HCW or delta wing dihedral angle increases but reduces as the anhedral angle increases. However, at the high angle of attack, the improvement of lateral stability may be limited while the delta wing has a large anhedral angle. As for the directional stability, the increase in HCW dihedral angle improves it, while HCW anhedral angle reduces it. In particular, the increase in both the dihedral and anhedral angles of the delta wing can improve the directional stability, but the effect of the anhedral angle is stronger.