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Abstract: In this study, an inward turning waverider forebody/inlet axisymmetric reference flow model with a conical leading-edge shock wave was designed based on the method of characteristics. The design eliminates the lip shock wave at the shoulder point. Based on the reference flow model, a novel integrated design method for an inward turning waverider forebody/inlet is proposed. The streamline tracing method and related technologies were used to generate the integrated configuration in the reference flow model. During the design process, the inward turning inlet was divided into an upper and a lower surface. After the formation of these surfaces, the front external surface and the lip external surface were simultaneously generated. Finally, an integrated configuration was formed with these four generated surfaces and a base plane. An analysis of the formed configuration was carried out using numerical simulation software, which verified the correctness and feasibility of the method. The conclusions drawn from the research indicate that the integrated design method is feasible and effective.

The authors present a novel methodology for designing inward turning inlets (ITI). The topic of ITI is of great interest in the hypersonic airbreathing community. The reviewer finds the paper to be well written. The authors show a high pressure recovery in their design. Challenging areas of design include off-design performance such as different Mach number and incidence angle, and viscous effects including shock/boundary layer interactions.

新型内转式乘波前体-进气道一体化设计方法

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