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Experimental investigation of supersonic flow with detached shock waves for Mach numbers between 1.8 and 2.9

机译：马赫数在1.8和2.9之间的超声冲击波超声波流动的实验研究

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Moeckel, W E;
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年度 1950
页码 1-57
总页数 57
原文格式 PDF
正文语种 eng
中图分类工业技术;
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1. A thorough experimental investigation of shock/shock interferences in high Mach number flows [J] . Serge M.Boldyrev, Volf Ya.Borovoy, Andrey Yu.Chinilov Aerospace science and technology . 2001,第3期

机译：对高马赫数流中冲击/电击干扰的全面实验研究
2. Shock wave control by dielectric barrier discharge and arc discharge in a Mach 2.2 cold supersonic airflow [J] . Jian Wang, Yinghong Li, Zhiyong An, International journal of applied electromagnetics and mechanics . 2010,第3a4期

机译：通过2.2马赫冷超音速气流中的介质阻挡放电和电弧放电控制冲击波
3. Experimental comparison of PIV-based pressure measurements in supersonic flows with shock waves [J] . Liu Shun, Xu Jinglei, Gong Hao, Measurement Science & Technology . 2019,第10期

机译：超声波流量的PIV基压力测量与冲击波的实验比较
4. Mach Reflection of Shock and Detonation Waves in Steady Supersonic Chemically Reacting Flows [C] . A. V. Trotsyuk, A. N. Kudryavtsev, M. S. Ivanov International Conference on Recent Advances in Space Technologies . 2003

机译：稳定超声波化学反应流的冲击和爆震波的马赫反射
5. AN EXPERIMENTAL INVESTIGATION OF SHOCK WAVES AND TURBULENT BOUNDARY LAYER INTERACTIONS IN A SUPERSONIC FLOWFIELD THROUGH AN ANNULAR DUCT (SCRAMJET). [D] . STOCKBRIDGE, RICHARD DREXEL. 1986

机译：通过环形管道（SCRAMJET）进行超音速流场中冲击波和湍流边界层相互作用的实验研究。
6. Experimental investigation on the characteristics of supersonic fuel spray and configurations of induced shock waves [O] . Yong Wang, Yu-song Yu, Guo-xiu Li, -1

机译：超音速燃油喷雾特性及激波配置的实验研究。
7. Study on Supersonic Internal Flows with Shock Waves : Investigation by Numerical Analysis on the Internal Structure of Mach 2 Pseudo-Shock Wave in a Two-Dimensional Channel [O] . 孫立群, 杉山弘, 溝端一秀, 2003

机译：具有冲击波的超声内部流动研究 - 二维通道中mach 2伪激波的内部结构数值分析研究
8. Flow characteristics over a lifting wedge of finite aspect ratio with attached and detached shock waves at a Mach number of 1.40 [R] . Hilton, John H , Jr 1952

机译：有限纵横比的提升楔上的流动特性，其中附加和分离的冲击波的马赫数为1.40

Experimental investigation of supersonic flow with detached shock waves for Mach numbers between 1.8 and 2.9

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