| Citation: | Li Yongzhou, Sun Di, Wang Renhua, et al. Geometric-flow synergistic design for low-Mach-number self-starting inward turning inlet[J]. Journal of Aerospace Power, 2026, 41（X）：20250452 doi: 10.13224/j.cnki.jasp.20250452
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A synergistic design method combining geometric configuration and flow control was proposed to enhance the low-Mach-number self-starting capability and mitigate vortex region in hypersonic inward-turning inlets. The method combined geometric reconstruction of “side wall segmentation, forward sweep, and outward translation” with a controlled side overflow strategy, significantly reducing the effective internal contraction ratio and achieving coordinated suppression and removal of separated flow and boundary layer. Three-dimensional numerical results show that, compared with the conventional rear-cut-lip configuration, the novel inlet achieves significant performance improvements over a wide Mach number range. The self-starting Mach number decreases from 3.9 to 3.2 and the starting Mach number decreases from 3.3 to 3.1. When the inflow Mach number is 4.0 and 6.0, the actual captured mass flow increases by 9.74% and 6.54%, respectively, and the exit total pressure recovery coefficient increases by 9.91% and 4.45%. Additionally, the exit distortion index is reduced by at least 13%, and at an inflow Mach number of 4.0, the vortex region is essentially eliminated.
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