Abstract
The porous opposing jet, one of the most practical strategies to reduce the aero-heating of forebody, is able to improve the overall characteristics of vehicle in supersonic/hypersonic flow. In order to reinforce the cognition about the drag reduction and thermal protection mechanism of porous opposing jet, the three-dimensional flowfield about porous jet is analyzed systematically by the numerical method. The obtained results show that there is a multi-stage shock train along the direction of blunt leading edge in the porous opposing jet flowfield. The interaction among adjacent shock waves is obvious. With the increase of jet total-pressure ratio, the shock stand-off distance enlarges and the vortex strength and recirculation region increase gradually. The flowfield structure is affected by the adjacent jet holes obviously and the blunt leading edge is covered by the recirculation region. That is very advantageous for hypersonic vehicle to achieve the effective thermal protection. The shapes about shock trains are almost the same on different Mach numbers conditions when PR keeps the same value. What's more, there is tight relationship between configuration parameters and free flow conditions to decide the flowfield structure, and there exists the optimal porous jet scheme to make the overall performance best.
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