A conical hypersonic vehicle with an overturned aerodynamic layout was accomplished and its aerodynamic performances were evaluated. In this work, the aerodynamic design methodology was addressed firstly, and then the conical vehicle integrated with an overturned inlet was obtained. The mass flow capture performance and the total pressure recovery performance were evaluated under design and off-design conditions. Results show that the mass flow capture increases and the total pressure recovery decreases as the inflow Mach number increases. The total pressure recovery decreases when the inflow Mach number increases. After that, the self-starting performance of the inlet was obtained by simulating an accelerating process. The initial inlet self-starts at Mach 5.2 on attack angle $6^{\circ }$ situation. Furthermore, an improvement of the inlet self-starting performance was achieved with keeping the designed mass flow capture almost constant. By altering the 3-D shape of the inlet leading edge, the inlet self-starting Mach number decreases from Mach 5.2 to Mach 4.6 on attack angle $6^{\circ }$ situation.

完成了一种具有翻转气动布局的锥形高超音速飞行器，并对其气动性能进行了评估。在这项工作中，首先解决了空气动力学设计方法，然后获得了带有翻转进气道的锥形车辆。在设计和非设计条件下评估质量流量捕获性能和总压力恢复性能。结果表明，随着流入马赫数的增加，质量流量捕获增加，总压力恢复减少。当流入马赫数增加时，总压力恢复减少。之后，通过模拟加速过程获得进气道的自启动性能。初始进气道以 5.2 马赫的迎角自启动$6^{\circ }$情况。此外，通过保持设计的质量流量捕获几乎恒定，实现了入口自启动性能的改进。通过改变进气道前缘的 3-D 形状，进气道自启动马赫数在攻角上从 5.2 马赫降至 4.6 马赫$6^{\circ }$ 情况。