Experimental study on the effects of the cone nose-tip bluntness

In this Letter, hypersonic boundary-layer transition was investigated on a large-scale cone with a height of 3 m and a half-cone angle of 7 degrees at a zero angle of attack in the JF-12 hypersonic flight duplicate shock tunnel. For the same freestream unit Reynolds number, with the increase in the bluntness Reynolds number, the transition Reynolds number has a trend of first increasing and then decreasing, showing a transition reversal phenomenon. As the bluntness increased, the high/low-frequency instability waves in the boundary-layer were modulated, which caused the boundary-layer transition to be delayed and then advanced. Published under an exclusive license by AIP Publishing.

Automated summary

This study investigates the hypersonic boundary-layer transition on a large-scale cone in a hypersonic flight duplicate shock tunnel. The transition Reynolds number shows a trend of first increasing and then decreasing with the increase in the bluntness Reynolds number, indicating a transition reversal phenomenon.