Hysteresis phenomena in fluid flow systems, in recent years, drew attention of many researchers towards industrial and engineering applications. From certain previous work in this field, it got clarified that when the high-pressure gas is exhausted to atmosphere from the nozzle exit, the expanded supersonic jet with the Mach disk is formed at a specific condition. In two-dimensional expanded supersonic jet, the hysteresis phenomenon for the reflection type of shock wave in the jet is occurred under the quasi-steady flow and the transitional pressure ratio between the regular reflection and Mach reflection in the jet is affected by this phenomenon. However, so far, there does not appear to be a significant progress made for the hysteresis phenomenon of shock waves in supersonic internal flow and the phenomenon has not been investigated satisfactorily. The present study pertains with experimental and numerical investigations of the hysteresis phenomena for the shock wave in a supersonic nozzle. The relationship between hysteresis phenomena for the location of shock wave in a supersonic nozzle and rate of the change of pressure ratio with time were experimentally investigated and discussed in this study. Moreover, experimental results were compared with some available numerically simulated data.