抄録
When the high-pressure gas is exhausted to the vacuum chamber from the nozzle, an underexpanded supersonic jet is generally formed. The jet structure is complex, involving the interaction of the several flow features, making this a demanding problem. Two types of shock reflection appear to occur in the jet structure, regular and Mack, depending on the jet pressure ratio. The existence of a dual solution domain is well known from regular and Mack reflection flow structure for two-dimensional flow. The purpose of this study is to clear the pressure-ratio-variation-induced hysteresis phenomenon of shock reflection type for an underexpanded supersonic jet. The numerical analysis is carried out in the region of exit Mach number from 1 to 2.5 , the axisymmetric conservational equation is solved by the TVD method in the numerical calculation. The results of the numerical calculation are used to clear the jet structure and compared with the results of hysteresis phenomena obtained by Gribben.
