초음속 노즐에서 발생하는 비대칭 유동의 제어에 관한 연구 = Control of the Asymmetric Flow in a Supersonic Nozzle

다국어 초록 (Multilingual Abstract)

Several previous works on rocket nozzle flows have revealed the existence 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 nozzle 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 experimentally investigated with the rate of change of the nozzle pressure ratio. The results obtained showed that the cavity system installed on nozzle wall would be helpful in fixing the unsteady motions of the boundary layer separation, consequently reducing the possibility of the occurrence of the asymmetric flow.

참고문헌 (Reference)

1 K. Yonezawa, "Suppression of Restricted Shock Separation in Overexpanded Rocket Nozzle" 71 (71): 2702-2709, 2005

2 Blair, A.J, "Supersonic Axial-Force Characteristics of a Rectangular-Box Cavity With Various Length-to-Depth Rations in a Flat Plate" NASA 1986

3 Y. Watanabe, "LE-7A Engine Nozzle Flow Separation Phenomena and a Method of RSS Suppression with a Step inside Nozzle" 55 (55): 474-482, 2007

4 K. Yonezawa, "A Study of Side Load in 2-D Nozzles during Shutdown" 69 (69): 1590-1598, 2003