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The three-dimensional inward-turning inlet has garnered widespread attention from aerospace researchers due to its advantages such as high compression efficiency and reduced wetted area. However, there is relatively limited research on inward-turning inlets at high Mach number. In this study, the "basic flow field + streamline tracing" method was employed to investigate the aerodynamic design of high Mach number inward-turning inlets. Numerical simulations were conducted to analyze the effects of typical design parameters, such as the initial compression angle of the basic flow field, the aspect ratio of the capture surface, and the relative radial position of the capture surface, on the aerodynamic performance of the inward-turning inlet. The results indicate that, in the design of high Mach number inward-turning inlets, increasing the initial compression angle offers significant advantages in optimizing configuration compactness and enhancing pressure rise capability. However, this also introduces irreversible total pressure losses due to the induction of higher-intensity shock waves. Increasing the aspect ratio of the capture curve can improve the pressure recovery. Appropriately shifting the capture surface outward can enhance the pressure rise capability, though it increases the length of the inlet.
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Basic Information:
DOI：10.16338/j.issn.2097-0714.20250129
China Classification Code:V211.48
Citation Information:
[1]Zhao Xuan,Wang Jian,Liu Jie.Study on the influence of design parameters on performance of inward-turning inlet[J].AEROSPACE TECHNOLOGY().DOI:10.16338/j.issn.2097-0714.20250129.
2026-05-22
2026-05-22
2026-05-22