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首页> 外文会议>International Symposium on Shock Waves >ISL Shock Tunnel Operation with Contoured Mach-4.5-6-8-10-Nozzles for Hypersonic Test Applications
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ISL Shock Tunnel Operation with Contoured Mach-4.5-6-8-10-Nozzles for Hypersonic Test Applications

机译：ISL冲击隧道运行，具有轮廓Mach-4.5-6-8-10-10-喷嘴，用于超声波测试应用

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摘要

Several design and flow characterization strategies for shock tunnel nozzles ranging from Mach 3 to 10 have been presented. A Mach 4.5 nozzle that was initially designed by the method-of-characteristics could be improved by CFD, which has advanced modelling capabilities for thermal and viscous effects. For a Mach 10 nozzle, it was demonstrated how different thermodynamic real-gas models could influence the simulated Pitot pressure distribution. The multiplicity of physical phenomena a simulation has to handle, however, still warrants the use of experimental verifications, such as Pitot surveys and PIV measurements. A future goal is to link the different methodologies closer together, in order to optimize the nozzle design process.
机译：已经提出了从马赫3到10的冲击隧道喷嘴的几种设计和流量表征策略。最初由特性方法设计的Mach 4.5喷嘴可以通过CFD提高，这具有用于热和粘性效果的先进的建模能力。对于马赫10喷嘴，证明了不同的热力学真实气体模型如何影响模拟的皮托压力分布。然而，仿真的多种物理现象必须处理，但仍然保证使用实验验证，例如皮特调查和PIV测量。未来的目标是将不同的方法联系在一起，以优化喷嘴设计过程。

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