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Investigation at Mach numbers 1.5 and 1.7 of twin-duct side intake system with two-dimensional 6 degree compression ramps mounted on a supersonic airplane

机译：在双管道侧进气系统的马赫数为1.5和1.7的情况下进行调查，其中二维6度压缩斜坡安装在超音速飞机上

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Davids, Joseph; Wise, George A;
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年度 1953
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;
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1. Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp [J] . Kim Ikhyun, Park Gisu, Byun Yung Hwan Journal of Mechanical Science and Technology . 2020,第10期

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2. Experimental Investigations of Supersonic Flow Over a Compression Ramp Based on Nanoparticle-Tracer-Based Planar Laser Scattering Technique [J] . Wu Y., Yi S., He L., Experimental Techniques . 2016,第2期

机译：基于纳米粒子跟踪器的平面激光散射技术在压缩坡道上超音速流动的实验研究
3. Experimental investigations of supersonic turbulent flow over a compression ramp [J] . Wu Yu, Yi Shihe, He Lin, Current Science: A Fortnightly Journal of Research . 2015,第2期

机译：压缩坡道上超音速湍流的实验研究
4. Q-DC Plasma Actuation for Mach-4 Supersonic Flow Control over Compression Ramp [C] . Yasumasa Watanabe, Skye Elliott, Alec Houpt, AIAA Scitech Forum and Exposition . 2020

机译：Q-DC等离子致动，用于Mach-4超音速压缩斜坡的流量控制
5. 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

Investigation at Mach numbers 1.5 and 1.7 of twin-duct side intake system with two-dimensional 6 degree compression ramps mounted on a supersonic airplane

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