Effect of Exit Geometry of Tail Pipe on the Performance of Pulse Jet Engines  

作　　者：Toshihiro NAKANO ShigeruMATSUO KenbuTERAMOTO ToshiakiSETOGUCHI 

机构地区：[1]Department of Mechanical Engineering,Saga University,1 Honjo-machi,Saga-shi,Saga 840-8502,Japan

出　　处：《Journal of Thermal Science》2006年第3期263-268,共6页热科学学报（英文版）

摘　　要：In this paper,the effect of geometries of tube open end on the shock,compression and expansion wavespropagating in the tube was investigated numerically and experimentally.One of them is a conventional straightshock tube with an open end.The other has a divergent tail tube at the exit.Applying a divergent tail tube(flaretube)to an open end shock tube,the period of one-cycle process could be shortened and the pressure behind theexpansion wave produced at the exit of the shock tube could be lowered much more below the atmosphericpressure than that produced in the straight tube.The results suggested that the intake air into the engine wassignificantly increased by applying a flare tube instead of a straight tube.

关 键 词：compressible flow shock wave expansion wave pulse jet numerical simulation 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]