EFFECT OF SUPERSONIC COUNTERFLOW JET ON BLUNT BODY HEAT TRANSFER RATES FOR ONCOMING HIGH ENTHALPY FLOW

Heat transfer reduction studies, in the presence of a supersonic counterflow jet from the stagnation point of a 60-degree apex angle blunt cone, are conducted in a free piston driven hypersonic shock tunnel, HST3, to verify the effectiveness of this technique for high enthalpy flows. For flow of Mach number 8 with stagnation enthalpy of 5 MJ/kg, it has been observed that the heat transfer rate at some location decreases initially with an increase in the injection pressure ratio until the critical injection pressure ratio is reached. Forty five percent reduction in heat transfer rate near stagnation point has been measured for the critical injection pressure ratio equal to 14.91. A further increase in the injection pressure ratio has reduced the overall percentage heat transfer reduction. Dependence of fluidic spike length on percentage heat transfer reduction has been confirmed.
Автор:  Kulkarni Vinayak , Reddy K. P. J.
Стр:  3