Combustion Characteristics of a Hypermixer Scramjet Engine-Mach 8 Experimental Study in HIEST--Reference-Cited by-同舟云学术

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Combustion Characteristics of a Hypermixer Scramjet Engine-Mach 8 Experimental Study in HIEST-

Published:2005 Issue:621 Volume:53 Page:467-481
ISSN:1344-6460
Container-title:JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
language:ja
Short-container-title:JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Author:

Sunami Tetsuji,Itoh Katsuhiro,Komuro Tomoyuki,Sato Kazuo

Publisher

Japan Society for Aeronautical and Space Sciences

Link

https://www.jstage.jst.go.jp/article/jjsass/53/621/53_621_467/_pdf

Reference23 articles.

1. 1) Murthy, S. N. B. and Curran, E. T. (eds.): High Speed Flight Propulsion Systems, AIAA Progress Series, 137, American Institute of Aeronautics and Astronautics, Washington, DC, 1991.

2. Compressibility Effects in Turbulent Shear Layers

3. The compressible turbulent shear layer: an experimental study

4. Considerations on Mixing and Combustion of a Scramjet Engine. Transition Processes from Weak to Intensive Combustion Mode.

Cited by 2 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Numerical Investigation of a Detonation Wave System in a Scramjet Combustor;18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference;2012-09-24

2. Mach 8 Ground Tests of the Hypermixer Scramjet for HyShot-IV Flight Experiment;14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference;2006-06-15

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