Observation of Unsteady Shock Motion Induced by Counterflow on a Blunt Body in Hypersonic Flow

초록

Experimental investigation about drag reduction with counter-flow jet have been carried out using hypersonic shock tunnel with freestream Mach number 7.0. Based on the experimental results such as surface pressure and flow visualization, the relation between penetration length and surface pressure have been verified. The results show that the penetration length is varied with time due to its fundamentally unsteady characteristics and the surface pressure on body is affected by not only penetration length but also unsteady shock motion.