Scramjet engines are one of the most promising hypersonic airbreathing propulsion technologies for robust, efficient, and economical access to space. Multi-objective design optimization has been conducted for Busemann-based intakes in inviscid and viscous regimes at single and multiple design points, respectively, by means of surrogate-assisted evolutionary algorithms coupled with computational fluid dynamics in the present research. Intake geometries are generated by applying geometric alterations to the full Busemann intake via leading-edge truncation, axial stunting, and radial contraction, aiming to simultaneously minimize intake drag and maximize the compression efficiency at two different design conditions (i.e., Mach 7.7 at an altitude of 30 km and Mach 10 at 33.5 km on a constant dynamic pressure ascent trajectory). The single-point inviscid optimization study has found that the nondominated solutions obtained from minimizing drag and maximizing compression efficiency are approximately the same as those obtained from maximizing total pressure recovery and minimizing static pressure ratio. From the multipoint viscous optimization study, the optimal solutions have been found to retain the original advantages of the inviscid full Busemann intakes in terms of high compression efficiency with shorter intakes and higher static pressure as well as adequately high mean exit temperature for both design conditions.

超燃冲压发动机是最有前途的高超音速吸气推进技术之一，可用于稳健、高效和经济地进入太空。在本研究中，通过代理辅助进化算法结合计算流体动力学，分别在单个和多个设计点对基于 Busemann 的进气口在无粘性和粘性状态下进行了多目标设计优化。通过前缘截断、轴向阻碍和径向收缩对完整的 Busemann 进气口应用几何改变来生成进气口几何形状，旨在同时最大限度地减少进气阻力并最大限度地提高两种不同设计条件下的压缩效率（即高度为 7.7 马赫）在恒定动态压力上升轨迹上的 30 公里和 10 马赫在 33.5 公里处）。单点无粘性优化研究发现，通过最小化阻力和最大化压缩效率获得的非支配解与通过最大化总压力恢复和最小化静压比获得的解大致相同。从多点粘性优化研究中发现，最佳解决方案保留了无粘性全布斯曼进气道的原始优势，即压缩效率高、进气口更短、静压更高，以及两种设计条件下的平均出口温度足够高。