ラバルノズルから噴出する超音速衝突噴流の数値解析

抄録

The objective of this study is to investigate the decreasing ambient pressure at nozzle exit. If there is a sudden expansion section in supersonic ow at the Laval nozzle exit, phenomenon of decreasing pressure will occur at the downstream. Using this phenomenon to decrease the ambient pressure, the cover that can expand the tube area is placed at nozzle exit. Mach number of ow through the inside of nozzle and cover increase as the ratio of stagnation pressure and ambient pressure rise up. In this paper, we present the results obtained from numerical analysis of ow expansion and increasing of Mach number by the cover and the decrease of the pressure at nozzle because of the difference in pressure ratio.