Experimental and computational investigation of the flow field of supersonic cavity with boosting nozzle is described. The purpose of boosting nozzle behind downstream of cavity is to decrease pressure drag of cavity. The other research tried to reduce this drag by changing rear wall design of cavity. And in this paper, we used boosting nozzle for same purpose. In our research, the boosting nozzle is located behind the rear wall of supersonic cavity flow.
For this purpose, we investigated supersonic cavity flow with boosting nozzle. Cavity flow in this research is of the open type, that is, length?to-depth ratio L/D is 3 and mach number of primary supersonic nozzle is 2.0, 2.5 with boosting nozzle mach number is 1.5 and 2.0. And we changed the ratio of mass flow rate of primary and boosting nozzle to compare the effect of boosting nozzle mach number and mass flow rate of both nozzle of efficiency of reduction of pressure drag of downstream of supersonic cavity flow. The ratio of mass flow rate of both nozzles is about 10 to 100.
Experiment is done with pressure measurement by pressure transducer and visualization by Schlirern method. At pressure measurement, we measured overall pressure distribution in the cavity by pressure transducer and measured pressure oscillation by piezo-type pressure sensor. And for visualization, we used Schlieren method th visualize the shock structure of supersonic cavity flow with boosting nozzle.
