高焓膨胀波管的气动实验  

Aerodynamic experiment of high enthalpy expansion tube

作　　者：施红辉[1] 王天军[2] 理查德.摩根 

机构地区：[1]中国科学院力学所,北京100080 [2]浙江教育学院物理系,杭州310012 [3]澳大利亚昆士兰大学机械工程系

出　　处：《空气动力学学报》2002年第4期483-486,共4页Acta Aerodynamica Sinica

基　　金：国家人事部留学人员科技活动择优项目(No.109301 N40292).

摘　　要：该研究简报介绍了用膨胀波管产生高超声速气流的实验结果。用压力传感器测量了激波管内的激波速度,用激光全息摄影拍摄了飞船返回舱模型吹风时的激波形状,证实了在膨胀波管中建立了可用的流动条件。This brief communication introduces an experiment of hypersonic flow using high enthalpy expansion tube. The velocity of the shock wave was measured by pressure transducers along the tube. The shape of shock wave around a capsule model was visualized by holographic interferometry. The experiment showed that usable test flow was obtained with the expansion tube. It is understood that the free piston driver and the evacuating are two key techniques in design and operation of expansion tubes.

关 键 词：膨胀波管 激波管 激波速度 空气动力学试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]