具备高超声速巡航能力的宽速域飞行器是近年来国内外的研究热点，然而，更宽的飞行速域给气动布局设计带来了巨大的挑战。本文旨在有效突破实用化升阻比与容积率之间的矛盾，基于高压捕获翼气动布局概念提出了一种具有大容积率特征的新型气动构型，仿真结果表明在马赫数6条件下最大升阻比可达5.89，相比于常规构型而言升阻比增量超过18%。在此基础上，以数值仿真为手段，重点针对马赫数0.8和1.2两个典型跨声速状态进行了计算。结果表明，相比于不带捕获翼的常规构型而言，本文所提构型在两种状态下的升力和阻力系数均有不同程度的增加。尽管升阻比有一定损失，但在整个宽速域范围内气动焦点的偏移量明显减小，在跨声速速域内焦点相对偏移量减小11.1%，在跨声速至高超声速速域内焦点相对偏移量减小49.9%。进一步分析表明，气动焦点偏移量的缩减主要是新增翼面与机身间的耦合作用所致。

In recent decades, wide-speed-range aircraft with hypersonic cruise capability have garnered significant attention and emerged as a prominent research focus both domestically and internationally. However, a wider flight velocity range poses significant challenges to aerodynamic configuration design. This study aims to effectively resolve the inherent trade-off between lift-to-drag ratio and volumetric efficiency in hypersonic vehicle design. A novel aerodynamic configuration with high volumetric capacity is proposed based on the high-pressure captured wing concept. Numerical simulations demonstrate that the maximum lift-to-drag ratio reaches 5.89 at Mach 6, representing an improvement exceeding 18% compared to conventional configurations. Based on this configuration, numerical simulations were performed focusing on two representative transonic conditions at Mach 0.8 and 1.2. The results demonstrate that compared to conventional configurations without captured wings, the proposed con-figuration exhibits increased lift and drag coefficients to varying degrees under both transonic conditions. Although some lift-to-drag ratio degradation is observed, the aerodynamic center shift is significantly reduced across the wide speed range. Specifi-cally, the relative shift decreases by 11.1% in the transonic regime and by 49.9% across the transonic-to-hypersonic regime. Fur-ther analysis reveals that the reduction in aerodynamic center shift is primarily attributed to the coupling effects between the additional wing surface and the fuselage.