Effects of Forebody Models and Internal Flow Supplying Methods on An Experimental Study of A Scramjet Asymmetric Nozzle
To investigate effects of interaction of an exhaust flow in a scramjet asymmetric nozzle with a hypersonic external flow on the nozzle performance, an experimental scheme which is planned to be performed in a hypersonic wind tunnel (M∞ =6) is discussed and designed Free stream in the wind tunnel constitutes the external flow to blow an experimental model which is composed of a forebody model and a nozzle model The experimental model is fixed on the side wall in the tunnel by a six freedom balance and a strut. The Mach number at the nozzle intake was designed to 1.5 and the pressure ratio at the nozzle exit was 54 to simulate the flight condition of Mach 6 at an altitude of 17km. To study effects of the forebody model on the external flow of the nozzle model, several simplified forebody model configurations are analyzed. It is found that the forebody model with a small attack angle may provide a more effective impact on the flowfield of the nozzle. Besides, to import gases to the nozzle model to simulate the exhaust flow and not bring an additional aerodynamic problem, cold or hot gas supplying methods are designed and discussed, and finally a direct tube structure with a perforated plate is believed to be fit for the experimental study.
scramjet asymmetric nozzle experiments wind tunnel
Yang Wenjiang He Miaosheng Zhang Wendian Qin Lizi Liu Yu
School of Astronautics, Beihang University, Beijing 100191, P.R.China School of Astronautics,Beihang University, Beijing 100191, P.R.China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
187-190
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）