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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.