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Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel

机译：研究Langley 11英寸高超声速隧道中单级二维喷嘴的流量

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Mclellan, Charles H; Williams, Thomas W; Beckwith, Ivan E;
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年度 1950
页码 1-31
总页数 31
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
NOZZLES, HIGH-PRESSURE; WIND TUNNEL APPARATUS - NACA - HYPERSONIC (11"); FLOW - NOZZLES; WIND TUNNELS - AIR FLOW; WIND TUNNELS - PRESSURE; WIND TUNNEL TESTS - NACA - HYPERSONIC (11");

机译：喷嘴，高压;风洞隧道设备 - NaCa - HYpERsONIC（11“）;流量 - 喷嘴;风洞 - 风量;风洞 - 压力;风洞测试 - NaCa - HYpERsONIC（11”）;

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专利

1. 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

机译：两相超音速冲击隧道在试验喷嘴和试验段的分散相流
2. 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

机译：粘性反应流的高超音速风洞喷嘴设计程序
3. Investigation of hypersonic nozzle flow uniformity using NO fluorescence [J] . OByrne S, Danehy PM, Houwing AFP Shock Waves . 2006,第2期

机译：使用NO荧光研究高超声速喷嘴的流量均匀性
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

机译：对高超声速风洞喷嘴中跨音速流动的影响进行实验和计算研究，包括滤波瑞利散射测量。
6. Two-Dimensional Automatic Measurement for Nozzle Flow Distribution Using Improved Ultrasonic Sensor [O] . Changyuan Zhai, Chunjiang Zhao, Xiu Wang, 2015

机译：使用改进的超声波传感器进行喷嘴流量分布的二维自动测量
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

Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel

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