Shaliang LI, Bing LIU, Shibin LI, Wei HUANG, Lin WANG

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST 2024- 0053

Hypersonic vehicles face extreme force/thermal environments, and the opposing jet could improve the thermal environment in its stationary/leading edge region through active flow control. In order to better understand influence and mechanism of porous opposing jet at rudder leading edge, a numerical simulation study is carried out, adopting fluid-thermal-structure two-way loose coupling method. Comprehensive analyses and comparisons are carried out, which of the drag reduction and thermal protection mechanisms of no-jet, single-hole jets and multi-hole jet. The influence of jet pressure ratio (PR), diameter (d) and spacing (G) of jet orifices on the thermal and structural responses are investigated in depth, which of the rudder leading edge porous opposing jet structure. The results show that porous opposing jet has better drag reduction and thermal protection effect than single-hole opposing jet, and the temperature distribution inside the thermal structure is more uniform. With increasing PR, the heat flux and temperature peaks of the rudder structure are lower, and the deformation of the solid structure is smaller, but the maximum stress increases substantially. There exists an optimal combination of structural parameters that makes the porous opposing jet structure the most efficient in terms of drag reduction and thermal protection. In the future work, we will mainly focus on its multi-objective design optimization.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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