Study on Hysteretic and Asymmetric Phenomena of Shock Wave Structure in Supersonic Nozzles

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In a supersonic nozzle(Laval nozzle), a shock wave is generated in the supersonic flow downstream of the nozzle throat in case ofφc<φ<φe(φ: ratio of back pressure to stagnation pressure of the wind tunnel,φe : minimum pressure ratio for choking at the nozzle throat,φc : pressure ratio in case with the shock wave at the exit of the Laval nozzle). Here, even if value ofφis the same in the processes of an increase and a decrease ofφ, the difference for shock wave structure(position and shape of the shock wave) is expected to arise. In this study, the hysteresis phenomenon for shock wave structure in supersonic nozzles was elucidated based on experimental and simulated results comprehensively and the effect of rate of the change of pressure ratio on the hysteretic phenomenon was indicated specifically. Further, the relationship of hysteretic and asymmetric phenomenon of shock wave structure was shown based on experimental results.