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Force test of a cold-wall blunt-nose cylinder- flare model in air-carbon-dioxide mixtures in the jpl 2-/inch hypersonic wind tunnel

机译：在jpl 2- / inch高超音速风洞中对空气 - 二氧化碳混合物中的冷壁钝头气缸 - 火炬模型进行力测试

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Hypersonic wind tunnel test of blunt-nose flared cylinder model for aerodynamic characteristics in air-carbon dioxide mixtures

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作者
Blaylock, R. B.;
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年度 1964
页码 1-42
总页数 42
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AERODYNAMIC CHARACTERISTICS; BLUNT BODIES; CARBON DIOXIDE; COLD SURFACES; DIOXIDES; FLARED BODIES; HYPERSONIC WIND TUNNELS; WALLS; WIND TUNNEL MODELS; WIND TUNNEL TESTS; AERODYNAMIC CHARACTERISTICS; BLUNT BODY; FLARED BODY; HYPERSONIC WIND TUNNEL; WIND TUNNEL MODEL;

机译：空气动力学特征; BLUNT BODIEs;二氧化碳;冷表面;二氧化物;贪婪的身体;超级风洞;墙;风洞模型;风洞隧道测试;空气动力学特征; BLUNT BODY;浑身脆弱; HYpERsONIC WIND TUNNEL;风洞模型;

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2. Pyrotechnic approach to space debris destruction: From thermal modeling to hypersonic wind tunnel tests [J] . Monogarov K. A., Melnikov I. N., Drozdov S. M., Acta astronautica . 2020,第Jula期

机译：烟火碎片破坏方法：从热建模到超音风隧道试验
3. A new dynamic modelling methodology of a force measuring system for hypersonic impulse wind tunnel [J] . Li Shichao, Li Kesi, Liu Bokai, Measurement . 2020,第1期

机译：超音速冲动风隧道力测量系统的一种新型动态建模方法
4. Thermal and Pressure Characterization of a Wind Tunnel Force Balance using the Single Vector System Experimental Design and Analysis Approach to Model Pressure and Temperature Effects in Hypersonic Wind Tunnel Research [C] . Keith C. Lynn, Sean A. Commo, Thomas H. Johnson, AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition . 2011

机译：基于单矢量系统的风洞力平衡的热压特性实验设计与分析方法，用于高超声速风洞研究中的压力和温度效应模型
5. Development and testing of a new optimum design code for hypersonic wind tunnel nozzles, including boundary layer, turbulence, and real gas effects. [D] . Tolle, Ralph Charles. 1995

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6. Hypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules [O] . Kazuhiko YAMADA, Masashi KOYAMA, Yusuke KIMURA, 2010

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7. Data Report of JPL wind tunnel tests of a 0.030-scale Apollo dynamic stability model (FD-1) in the 20-inch supersonic (test no. 20-516) and the 21-inch hypersonic (test no. 21-113) tunnels [R] . 1963

机译：在20英寸超音速（测试号20-516）和21英寸高超音速（测试号21-113）隧道中的0.030比例apollo动态稳定性模型（FD-1）的JpL风洞试验数据报告

Force test of a cold-wall blunt-nose cylinder- flare model in air-carbon-dioxide mixtures in the jpl 2-/inch hypersonic wind tunnel

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