This paper proposes an inward-turning-inlet–forebody integration methodology based on the dual-waverider concept. For the design concept and the designed flight conditions, both the airframe and inlet benefit from the waverider's high lift-to-drag ratio and the ideal compression performance of its propulsion system. The critical issue is to construct a complex three-dimensional shock wave that accounts for both the inlet and airframe. A method is then proposed for connecting the axisymmetric flow fields of the internal and external flows. The compression surface of the integrated vehicle is then generated from the streamlines obtained with a series of axisymmetric basic flows. Finally, the integration configuration is verified using computational methods, and its viscous effects are analyzed under both on- and off-design conditions via numerical simulations. The results show that a configuration designed using the proposed approach has a high corresponding lift-to-drag ratio and high hypersonic inlet performance.

本文提出了一种基于双波导管概念的向内进气-人体集成方法。对于设计概念和设计的飞行条件，机身和进气口均受益于Waverider的高升阻比以及其推进系统的理想压缩性能。关键问题是构造一个复杂的三维冲击波，该冲击波要同时考虑进风口和机身。然后提出一种用于连接内部和外部流的轴对称流场的方法。然后，从通过一系列轴对称基本流获得的流线生成集成车辆的压缩面。最后，使用计算方法验证集成配置，并通过数值模拟在设计时和设计外条件下分析其粘性影响。结果表明，使用提出的方法设计的配置具有较高的相应的升阻比和高超声速进气性能。