Counterflow drag reduction by supersonic jet for a blunt body in hypersonic flow

Counterflow drag reduction by supersonic jet for a large angle blunt cone at hypersonic Mach number is investigated in a shock tunnel. The flowfields around the test model in the hypersonic flow with an opposing supersonic jet emanating from the stagnation point of the model are visualized by high speed schlieren technique. The aerodynamic drag force is measured using the accelerometer based force balance system. The experimental measurements show about 30%-45% reduction in drag coefficient for different jet pressures. (c) 2006 American Institute of Physics.