With the continuous expansion of the flight speed and altitude envelopes of air-breathing hypersonic vehicles, the core technical challenges faced by solid powder scramjets have shifted from simply pursuing improved blending combustion efficiency to deeper wave system regulation and flow control. Based on the Euler-Lagrange framework, a numerical model and method are established for compressible gas-solid two-phase turbulent flow, investigates the flow control mechanism of powder fuel pre-injection in a wide-speed-range inlet, and analyzes the influence mechanisms of different incoming flow Mach numbers (4–7) and powder fuel transport solid-gas ratios (2.0–14.0) on the flow characteristics, performance, and powder fuel mixing process of the inlet. Through a systematic analysis of the interaction mechanism between the inlet wave system structure and the boundary layer under pre-injection, it is found that pre-injection can reconstruct the wave system structures of the internal and external compression sections, which improves the inlet pressurization performance while also reducing the total pressure recovery performance. By establishing the intrinsic correlation between the transport solid-gas ratio and the mixing efficiency of powder fuel, the formation mechanisms of the high vorticity region in the gas-solid two-phase shear layer, the high vorticity region in the wake, and the particle phase stagnation region at the shoulder are revealed, and the particle dispersion characteristics and the evolution laws of the vortex structure in the above regions are clarified.

Compared with conventional vehicles, waverider is expected to overcome the limitations of lift-to-drag ratio in hypersonic conditions and considered one of the most promising configurations for hypersonic vehicles. Typically, waverider exhibits good aerodynamic performance under the design condition. However, maintaining such performance under off-design condition is challenging, leading to insufficient aerodynamic performance across a wide range of speed. This paper first proposes a novel design method for double swept waverider, where lift exhibits nonlinear growth with an increasing angle of attack and generates strong surface vortex lift at low speeds. These characteristics effectively accommodate both high-speed and low-speed conditions, improving waverider performance under off-design condition across a wide range of speed. The curved-cone-derived waverider design based on the projection approach enables simultaneous control of the basic flow field and planform contour, addressing the limited design space issue of conventional methods while enhancing aerodynamic performance under the design condition. Furthermore, to achieve optimal wide-speed-range performance, an aerodynamic estimation method is developed and combined with an improved multi-objective cuckoo search algorithm for optimization. Subsequently, the numerical method is applied to the optimized representative configurations under the hypersonic condition and the expected aerodynamic performance is obtained. The subsonic aerodynamic performance of waverider is also investigated. The double swept waverider in this research generates strong vortex lift and ideal longitudinal static stability performance at subsonic speed, which optimizes the wide-speed-range aerodynamic performance.