Study on Experimental Technique for Supersonic Combustion

通常人们需要大型设施来进行超燃冲压发动机的实验。在大学规模的实验室中进行超声速燃烧的研究，必须研制小型实验装置。从这些角度出发，我们计划与德国亚琛莱茵-威斯特伐利亚理工大学合作开发这种系统的可能性。在过去的3年里，我们邀请了亚琛莱茵-威斯特伐利亚理工大学冲击波实验室的3名研究人员，并派遣了3名教授到他们的实验室。交流了横滨国立大学的超音速燃烧结果和亚琛工业大学的超音速流测量技术。在三年的时间里，我们可以得到以下结果：1。（模型I）（1）在横滨国立大学热物理实验室，我们在入射激波中获得了马赫数为2的流动，并使用扩张喷管将流动加速到马赫数为5。我们从下游侧传爆轰波，观察到爆轰波传播速度的降低。（2）利用这些结果，我们设计了一个较大的实验装置，以获得马赫数为6-7的超声速流场。目前在亚琛这个超音速风洞正在建设中。在这个项目之后，我们计划开发一个实验，以获得持久的爆炸.（型号II）我们在横滨制造了拉伐尔喷管，以获得马赫数5。（1）利用该喷管，我们测量了流速（马赫数）等：（1.1）根据滞止压力和静压，我们计算了喷管中的马赫数。（1.2）利用Nano-spark光源拍摄了纹影照片和阴影照片，并利用斜激波的角度测量了马赫数5。（1.3）我们通过在流中接种的小颗粒的消光直接测量流速，并获得600-700 m/s，其对应于马赫数5。

Usually one needs large facilities for the experiments of the SCRAM-JET. When studying the supersonic combustion in the laboratory of university-size, one has to develop the facilities of small size. From these points of view we planned the project to find any possibilities to develop such system under co-working with Rheinisch-Westfaelische Technische Hochschule Aachen in Germany.During the past 3 years of this project we invited three researchers from the shock wave laboratory in RWTH Aachen and sent three professors from our side to their laboratory. The results of supersonic combustion at Yokohama National University and the technique of supersonic flow measurements at RWTH Aachen were exchanged. In three years we could obtain the following results :1.(Model I)(1)In the Laboratory of Thermophysics at Yokohama National University we obtained the flow of Mach-number 2 in the incident shock wave and accelerated the flow using divergent nozzle until Mach-number 5. We propagated the detonation from the side of down stream and observed decrease of the propagating velocity of detonation. (2)Using these results we designed a larger facility to obtain the supersonic flow of Mach-number 6-7. Presently in TH Aachen this supersonic wind tunnel is being built. After this project we plan to develop an experiment to obtain the standing detonation.2.(Model II)In Yokohama we built the Laval-nozzle to obtain Mach-number 5. (1)Using this nozzle we measured the flow velocity (Mach-number) etc. : (1.1)From the stagnation and static pressures we calculated Mach-number in the nozzle. (1.2)We took the Schlieren and shadow photographs by using Nano-spark light source and measured Mach-number 5 using the angle of the oblique shock wave. (1.3)We directly measured the flow velocity by light extinction of small particles seeded in the flow, and obtained 600-700 m/s, which corresponded to the Mach-number 5.