Abstract:The three-dimensional compression scramjet inlet has been investigated by using surface oil dot visualization and numerical simulation. The research has revealed the details of the internal flow pattern, which included the structure of the shock waves, the spillage, the spatial vortical structures, and the boundary layer separations etc.. These features determined the performance of the inlet, which gave the mass flow capture ratio of 0.86, total pressure recovery of 0.41. The results showed that the arrangement of the shocks is critical for such kind of inlet. More researches have been carried out to investigate the effect of the cowl shape, and the results showed the flow field would be changed little for the cowls with different shapes but the same internal contraction ratios.

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