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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冲击隧道操作，轮廓高的Mach-4.5-6-8-10-喷嘴，用于超音速测试应用

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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3马赫至10马赫的冲击隧道喷嘴的几种设计和流量表征策略。最初通过特性方法设计的Mach 4.5喷嘴可以通过CFD进行改进，CFD具有针对热和粘性效应的先进建模功能。对于10马赫的喷嘴，已证明了不同的热力学实际气体模型如何影响模拟的皮托管压力分布。但是，仿真必须处理的多种物理现象仍然需要使用实验验证，例如皮托管调查和PIV测量。未来的目标是将不同的方法学联系在一起，以优化喷嘴设计过程。

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