Abstract
Counterflow drag reduction by supersonic jet for a 60° apex angle blunt cone flying at hypersonic Mach number is investigated for two different flow enthalpies using conventional and free piston driven hypersonic shock tunnels. Enhancement in drag reduction has been observed with increase in freestream stagnation enthalpy. It is shown that the percentage of drag reduction goes up by a factor of 2 when the flow enthalpy increases by a factor of 2.5 for a given ratio of total pressure of supersonic jet and freestream flow.
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