| Citation: | HU Chenhao, SUN Haotian, ZHANG Jianwei, et al. Effects of transpiration cooling on flow structure and aerothermal environment of high Mach number compression corner[J]. Journal of Aerospace Power, 2026, 41（X）：20250471 doi: 10.13224/j.cnki.jasp.20250471
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In order to meet the thermal reduction requirements of high Mach number compression corners, numerical simulations were carried out to study the effects of gas transpiration on the flow structure and aerothermal environment of a 15° compression corner at a free stream Mach number of 11.63. The results showed that gas transpiration significantly increased the boundary layer thickness in both its active and downstream regions, reduced the velocity gradient within the boundary layer, and augmented the local pressure. When the transpiration location was positioned upstream or within the separation zone, gas transpiration led to a significant enlargement of the separation region. In contrast, when the transpiration location was positioned downstream the separation zone, gas transpiration had a negligible influence on the separation characteristics. Variations in the flow structure were found to significantly influence the wall heat flux distribution. The thickening of the boundary layer reduced the temperature gradient within it, thereby lowering the wall heat flux in both the transpiration region and the downstream region. To achieve optimal thermal reduction, transpiration cooling should cover the high heat flux region near the peak heat flux, while its effect remains confined to the downstream region to prevent the expansion of the separation zone, thereby stabilizing the peak heat flux location and effectively reducing the peak heat flux.
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