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1 Non-Intrusive Characterization of the Ionized Flow Produced by Nozzle of an Hypersonic Wind Tunnel

机译：1高超声速风洞喷管产生电离流的非侵入特征

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C. A. Borghi; A. Cristofolini; M. R. Carraro; F. Paganucci;
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1. Hypersonic Wind Tunnel Nozzle Design Procedure for Viscous Reacting Flow [J] . Frederick L. Shope The ITEA Journal of Test and Evaluation . 2005,第1期

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2. NUMERICAL DESIGN OF MULTIMODAL AXISYMMETRIC HYPERSONIC NOZZLES FOR WIND TUNNELS [J] . S. M. Aulchenko, V. M. Galkin, V. I. Zvegintsev, Journal of Applied Mechanics and Technical Physics . 2010,第2期

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3. FLOW OF A DISPERSED PHASE IN THE LAVAL NOZZLE AND IN THE TEST SECTION OF A TWO-PHASE HYPERSONIC SHOCK TUNNEL [J] . A. A. Verevkin, Yu. M. Tsirkunov Journal of Applied Mechanics and Technical Physics . 2008,第5期

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4. Non- Intrusive Characterization of the Ionized Flow Produced by Nozzle of an Hypersonic Wind Tunnel [C] . C. Borghi, A. Cristofolini, M. Carraro, 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference . 2006

机译：高超声速风洞喷嘴产生的电离流的非侵入式表征
5. An experimental and computational investigation on the effect of transonic flow in hypersonic wind tunnel nozzles, including filtered Rayleigh scattering measurements. [D] . Boyd, Robert Raymond. 1996

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6. Fabrication and Hypersonic Wind Tunnel Validation of a MEMS Skin Friction Sensor Based on Visual Alignment Technology [O] . Xiong Wang, Nantian Wang, Xiaobin Xu, 2019

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7. Part I. The effect of a simple throat distortion on the downstream flow in a hypersonic wind tunnel nozzle. Part II. An experimental investigation of flow over simple blunt bodies at a nominal Mach number of 5.8 [O] . Oliver Robert E. 1957

机译：第一部分。高超声速风洞喷嘴中简单喉部扭曲对下游流动的影响。第二部分。标称马赫数为5.8的简单钝体流动的实验研究

1 Non-Intrusive Characterization of the Ionized Flow Produced by Nozzle of an Hypersonic Wind Tunnel

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