Static Cylinder as a Base Pressure Controller in Supersonic Regime

Abstract

An experimental study for over expanded, perfectly-expanded and under-expanded supersonic jets at Mach 2 is presented to study the effectiveness of a static cylinder to reduce base drag. A static cylinder of diameter 2 mm located at 2 mm from the sidewall of a square duct and 8 mm from the converging-diverging square nozzle exit in the base region is installed as a passive control device. Base pressures in the wake flow after a sudden expansion of jets into a square nozzle have been measured. The length-width ratio of the duct is 10. The jets were operated at different nozzle pressure ratios in the range from 2 to 9. The flow field in the square duct was also observed for all cases. The static cylinder as a passive controller was found to reduce the base drag as high as 59 percent at NPR = 9 and 14 percent at NPR = 6. The base pressure depends on Mach number, area ratio, length to width ratio, and nozzle pressure ratio. When the flow from the nozzle is over expanded, the static control is ineffective till NPR is 6. The level of expansion plays a vital role. The flow flux in the square duct remains almost identical with and without control for most of the cases. However, at higher NPRs namely 6, 7.8, and 9 the control results in an increase as well as a decrease in the wall pressure along the duct. Passive control of the base flow is effective for higher NPRs. The flow field for higher NPR is dominated by the shock waves. Further, this phenomenon is visualized using a shadowgraph.