| Citation: | DAI Gang, ZHAO Wenwen, YANG Fan, et al. Numerical assessment of aerothermal environment of three-dimensional gap coupled with heat transfer of solid field[J]. Journal of Aerospace Power, 2025, 40（1）：20230006 doi: 10.13224/j.cnki.jasp.20230006
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In order to study the influence of the surface gap or grooves on hypersonic aircraft the aerothermal environment and the thermal protection system design, a numerical simulation method coupled with heat transfer of solid field was constructed. The numerical simulation analysis of the perfect gas flow passing a two-dimensional gap, original and reversed “T”-shaped three-dimensional gaps was carried out for isotherm and distributed temperature surfaces coupled with heat transfer of solid field. It can be found from the numerical results that the aero-heating effect at the corner of the rear facade of the two-dimensional and three-dimensional gaps was the worst. There were heat flux peaks at the side of the horizontal and vertical intersections of the original and reversed “T” shaped gaps. The airflow directly impacted the rear facade on the horizontal and vertical intersections of the “T”-shape gap, where a peak of aerodynamic heat flux of 26.18 W/cm2 of the entire gap was produced. Due to the vortex structure in the gap, a local heat flux peak value of 6.125 W/cm2 was generated on the front facade at the horizontal and vertical intersections of the reversed “T”-shape gap. Considering the influence of the coupled heat transfer of solid field, the wall temperature roses under the action of aero-heating, which reduced the heat conduction effect of the high-temperature gas in the flow field on the wall. Therefore, the overall heat flux distributed inside the gap, on facade at the side of the gap and on the upper surface of the gap was reduced by about 25%, and the peak value at the inflection point on the rear elevation decreased the most by about 32.04%.
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