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Shigeru Matsuo,Toshiaki Setoguchi,Junji Nagao,Miah Md. Ashraful Alam,김희동 대한기계학회 2011 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.25 No.10
In recent studies on two-dimensional supersonic jets, it is reported that the hysteresis phenomenon for the reflection type of shock waves in the jet flow field is occurred under the quasi-steady flow condition and this phenomenon is affected by the transitional pressure ratio between the regular reflection and Mach reflection. However, so far, there are few researches on the hysteresis phenomenon for the transition of shock waves between regular and Mach reflection in over-expanded supersonic jets and the phenomenon has not been investigated satisfactorily. Therefore, the purpose of this study is to clarify the hysteresis phenomena for the reflection type of shock wave in the over-expanded axi-symmetric supersonic jet experimentally, and to discuss the relationship between hysteresis phenomenon and rate of the change of pressure ratio with time. Furthermore, the effect of Mach number at the nozzle exit on hysteresis loop was investigated for two kinds of nozzle.
Control of the Asymmetric Flow in a Supersonic Nozzle
Shigeru Matsuo,Toshiaki Setoguchi,Tokitada Hashimoto,Seiya Tokuda,Junji Nagao,Heuy-Dong Kim(김희동) 한국가시화정보학회 2011 한국가시화정보학회지 Vol.9 No.2
Several previous works on rocket nozzle flows have revealed thc existencc of the transition from FSS to RSS and the occurrence of asymmetric flow associated with the boundary layer separation, which can cause excessive side-loads of the propulsion system. Thus, it is of practical importance to investigate the asymmetric flow behaviors of the propulsion nozzlc and to develop its control method. In the present study, the asymmetric flow control method using a cavity system was applied to supersonic nozzle flow. Time-dependent asymmetric flow was experimcntally investigated with the rate of change of the nozzle pressure ratio. The results obtained showed that the cavity systcm installed on nozzle wall would be helpful in fixing the unsteady motions of the boundary layer separation, consequcntly reducing the possibility of the occurrence of the asymmetric flow.