IMECH-IR  > 高温气体动力学国家重点实验室
Starting Process in a Large-Scale Shock Tunnel
Wang YP(汪运鹏); Hu ZM(胡宗民); Liu YF(刘云峰); Jiang ZL(姜宗林)
Source PublicationAIAA Journal

The starting process of the flow in an expansion nozzle (nominal Mach number 6) with an outlet diameter of 1.5 m and 8.9 m length, which is used for a large-scale hypersonic shock tunnel in the Key Laboratory of High-Temperature Gas Dynamics, was simulated and analyzed at incident Mach number M-s = 3.9. The calculating domains include the driven section (the shock-tube end, about 4.8m length), the nozzle with about 8.9 m length, and part of the test section (more than 3 m). The characteristics of unsteady nozzle flow, including the shock wave patterns in the nozzle inlet region and inside the nozzle, were analyzed numerically in the viscous and inviscid flow regimes, respectively. The pressure and Mach number results were presented and discussed by comparing with the experimental findings, where the simulated results of the reflected shock wave in the shock tube and the transmitted shock wave inside the nozzle were found to agree well with the test data. Additionally, the case without a contraction section for the throat configuration was also calculated and compared with the case with a contraction section. The effect of the starting flow in these two cases on the flowfield uniformity is discussed in detail in this paper.

Indexed BySCI ; EI
WOS IDWOS:000374877600009
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Cited Times:5[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
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GB/T 7714
Wang YP,Hu ZM,Liu YF,et al. Starting Process in a Large-Scale Shock Tunnel[J]. AIAA Journal,2016,54(5):1240-1249.
APA Wang YP,Hu ZM,Liu YF,&Jiang ZL.(2016).Starting Process in a Large-Scale Shock Tunnel.AIAA Journal,54(5),1240-1249.
MLA Wang YP,et al."Starting Process in a Large-Scale Shock Tunnel".AIAA Journal 54.5(2016):1240-1249.
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