Attenuation of incident shock waves in free piston shock tunnels

被引：0
|
作者：
Zhu H. [1 ]
Jiang H. [1 ]
Zhang B. [1 ]
机构：
[1] China Academy of Aerospace Aerodynamics, Beijing
来源：
Zhu, Hao (13439821690@163.com) | 1600年 / Chinese Society of Astronautics卷 / 38期
基金：
中国国家自然科学基金;
关键词：
Attenuation; Compression tube; Free piston shock tunnel; Incident shock wave; Safe velocity;
D O I：
10.7527/S1000-6893.2017.121328
中图分类号：
学科分类号：
摘要：
Attenuation of incident shock waves in free piston shock tunnels is of great important, which not only reduces the enthalpy, pressure and steadiness, but also imposes constraints on valid testing time. In this study, an attempt of investigation of main reasons of attenuation of shock wave was carried out based on the structural features of free piston tunnels. After neglecting some random factors, two important factors of attenuation, viscosity of the boundary layer and the reflected expansion wave, were studied. The results show that the latter factor plays major role in free piston shock tunnels. When the main diaphragm ruptures, the front face of the piston is very close to the main diaphragm, which leads to reflected expansion wave to catch up with the interface or shock wave earlier. A new compression tube with an abrupt area change was proposed, which can delay the interaction between the reflected expansion wave and the interface (or shock wave). In the new compression tube, the steady pressure and temperature of driver gas could be formed in the end of the tube while the free piston decelerated to a safety speed. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.
引用
收藏
相关论文
共 20 条
  • [11] Trimpi R.L., Nonlinear theory for predicting the effects of unsteady laminar, turbulent, transitional boundary layers on the attenuation of shock wave in a shock tube: NASA TN 4347, (1958)
  • [12] Emrich R.J., Wheeler D.B., Wall effect in shock tube flow, Physics of Fluids, 1, 1, pp. 14-23, (1958)
  • [13] Spence D.A., Woods D.A., Boundary layer and combustion effects in shock tube flows, Hypersonic Flows, 11, 3, pp. 163-180, (1960)
  • [14] Anderson G.F., Murthy V.S., Attenuation of the shock in a shock tube due to effect of wall boundary layer: AIAA-1968-0053, (1968)
  • [15] Muylaert J., Voiron R., Sagnier G., Et al., Review of the European hypersonic wind tunnel performance and simulation requirements, Proceedings of the First European Symposium on Aerothermodynamics for Space Vehicles, pp. 559-574, (1991)
  • [16] Jacobs P.A., Quasi-one-dimensional modeling of free piston shock tunnel, AIAA Journal, 32, 1, pp. 137-145, (1994)
  • [17] Srinivasan S., Tannehill J.C., Simplified curve fits for the thermodynamic properties of equilibrium air: NASA-CR-178411, (1987)
  • [18] Doolan C.J., Modeling mass entrainment in a quasi-one-dimensional shock tube code, AIAA Journal, 34, 6, pp. 1291-1293, (1996)
  • [19] Hornung H.G., The piston motion in a free piston driver for shock tubes and tunnels: GAL. CIT Rep. FM88-1, (1988)
  • [20] Labracherie L., Dumitrescu M.P., Burtschell Y., Et al., On the compression process in a free-piston shock-tunnel, Shock Waves, 3, 1, pp. 19-23, (1993)
12