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Heat transfer characteristics in a parallel loop type thermosyphon

Autor: Kaminaga, Fumito, Watanabe, Hideaki, Matsumura, Kunihito

Publikováno v: 宇宙航行の力学シンポジウム平成14年度 = Symposium on Flight Mechanics and Astrodynamics 2002. :135-138

資料番号: AA0045913035

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::d04a1c88e2f0e7636bc767bc6a4ca12c
http://id.nii.ac.jp/1696/00014716/

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Analysis of a supersonic flow using the moment equation

Autor: Soga, Takeo, Natsume, Hiromitsu

Publikováno v: 宇宙航行の力学シンポジウム平成14年度 = Symposium on Flight Mechanics and Astrodynamics 2002. :39-42

資料番号: AA0045913011

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::95b1a8907c02ba6e0b5f0338c01c4b97
http://id.nii.ac.jp/1696/00014692/

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固体ロケットモータのノズル壁に対する熱評価

Autor: Daimon, Yu, Matsuo, Akiko

Publikováno v: 航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001. 53:309-314

The flowfields in solid rocket motor of gas-particle mixture are simulated for the estimation of heat transfer for the solid rocket motor nozzle. Eulerian approach is used in the solid phase computations. The heat flux on the nozzle wall consisting o

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::845f1a88bad9938ec6dc3b2558124cd8
http://id.nii.ac.jp/1696/00038083/

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Autoignited combustion performance in a water-cooled scramjet combustor

Autor: Murakami, Atsuo, Kudo, Kenji, Hiraiwa, Tetsuo, Chinzei, Nobuo, Kanda, Takeshi

Publikováno v: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report.

水冷スクラムジェット燃焼器の自発着火燃焼性能を、空気総圧、空気総温、燃焼器長さ、壁温そして燃料噴射型式をパラメータとして調べた。水冷スクラムジェット燃焼器には、マッハ�

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::af3f2d7b60d9d498842c8e402c18f3c8
http://id.nii.ac.jp/1696/00002338/

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Numerical study of mixing and combustion process of a scramjet engine model

Autor: Masatoshi Kodera, Kazuhiro Nakahasi, Tetsuji Sunami

Publikováno v: 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference.

In this study, a numerical analysis of combusting flows was made on the scramjet engine which has been tested at Ramjet Engine Test Facility (RJTF) of National Aerospace Laboratory of Japan. The main purpose is to numerically investigate the physical

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=doi_dedup___::1cd7bf2c362247a55daa73c0cb656620
https://doi.org/10.2514/6.2001-1868

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Experimental study on relation between boiling heat transfer and flow behavior in microtube

Autor: Huang, Shih-Che, Kawanami, Osamu, Honda, Itsuro, Kawashima, Yosuke, Ota, Haruhiko

Publikováno v: 宇宙利用シンポジウム第24回平成19年度 = Space Utilization Research: Proceedings of the Twenty-fourth Space Utilization Symposium. :210-211

For the detail study on forced convective boiling heat transfer in mini- and micro-tube, we developed the transparent heated mini- and micro-tube by electroless deposition. The inner wall of the tube is coated with the thin gold film, which allows th

Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::483c086c063495977606abaa4ee416e9
http://id.nii.ac.jp/1696/00013422/

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