Zobrazeno 1 - 10 of 15 pro vyhledávání: '"燃焼効率"'
1
Pre-flight analysis of scramjet flight experiment by CFD
Autor: Kodera, Masatoshi, Sunami, Tetsuji, Ito, Katsuhiro
Publikováno v: 宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集 = JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005. :221-226
In this study, CFD has been applied to the prediction of the characteristics of two scramjet engines that will be tested at Mach 8 in JAXA's flight program for 2005. The engines each has the Hyper Mixer (HM) injector, which generates streamwise vorti
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::522fa023254a4a1fdeadc5a09c31778f
http://id.nii.ac.jp/1696/00006164/
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2
Research and development of ejector rocket for combined cycle engine: Research of rocket engine with variable combustion pressure and variable mixture ratio
Autor: Takegoshi, Masao, Tomioka, Sadatake, Ueda, Shuichi, Saito, Toshihito, Izumikawa, Muneo
Publikováno v: 宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems. :75-80
A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit to a Rocket-Based-Combined-Cycle engine model, and its performances were evaluated experimentally. The rocket chamber was required to operate at a very wide operation range in terms
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::27d9a1d21765ee6e7e26bfd844fea711
http://id.nii.ac.jp/1696/00006241/
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3
Measurements of combustion efficiency in engine wind tunnels
Autor: Mitani, Toru
Publikováno v: 宇宙航空研究開発機構特別資料: 第73回風洞研究会議論文集 = JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 73rd Meeting. :39-49
資料番号: AA0048471006
レポート番号: JAXA-SP-04-014
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::f7786c654e4588003950d234ec52c2bd
http://id.nii.ac.jp/1696/00006424/
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4
Numerical analysis of ignition and flameholding by plasma torch in supersonic airflow
Autor: Minato, Ryojiro, Niioka, Takashi
Publikováno v: 宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2004論文集 = JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2004. :224-229
The purposes of the present study were to clarify the three-dimensional structure of hydrogen flame reinforced by a plasma torch and to analyze the effect of the position of a hydrogen jet relative to the plasma torch on the combustion characteristic
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::42890f3a6f9e86e6cd1db3ea4d932cb4
http://id.nii.ac.jp/1696/00006472/
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6
Working characteristic analysis of a scramjet engine with sidewall and ramp compression by CFD
Autor: Kodera, Masatoshi
Publikováno v: 宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集 = JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003. :119-124
A scramjet engine model with sidewall and ramp compression (called E2R) indicated better engine performance than a conventional sidewall compression type engine under the Mach 8 flight condition in the firing tests at Ramjet Engine Test Facility (RJT
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::f180f085993da1b1412d3b31299cf661
http://id.nii.ac.jp/1696/00006617/
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7
液体燃料ラムジェット燃焼器の噴霧および燃焼特性
Autor: Sasaki, Masaki, Takahashi, Mamoru, Sakamoto, Hiroshi, Kumakawa, Akinaga, Yatsuyanagi, Nobuyuki, Sei, Motohiro, Yoshimura, Kazuhiko, Inamura, Takao
Publikováno v: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory. :1-16
炭化水素燃料を用いるラムジェットやロケット-ラムジェット複合燃焼器の設計に資することを目的として、炭化水素燃料の高温・高速気流中における微粒化特性および燃焼特性について
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::f33af762da153ad6475598d3ee96692e
http://id.nii.ac.jp/1696/00040297/
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8
Numerical simulation of hydrogen/oxygen turbulent combustion flows
Autor: Mizobuchi, Yasuhiro, Ogawa, Satoru
Publikováno v: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory. 37:51-56
航空宇宙技術研究所 12-13 Jun. 1997 東京 日本
National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan
水素・酸素乱流燃焼による流れ場を数値シミュレーションした。混合および化学反応での乱
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::621d29c16f18bb4bf871700ce0cc1790
http://id.nii.ac.jp/1696/00037128/
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9
Combustion characteristics of LOX-hydrogen with high mixture ratio, 1
Autor: Sakamoto, Hiroshi, Sasaki, Masaki, Takahashi, Mamoru, Sato, Kazuo, Tamura, Hiroshi
Publikováno v: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory. 1278:1-15
単段式宇宙往還機(SSTO)に用いるデュアル混合比液体酸素(LOX)-水素エンジンを提案した。このエンジンは、離陸時には高混合比で作動させてブースタモードで高い密度比推力を得、高空で
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::2545d57ade777c5bb25e40a891d4ecce
http://id.nii.ac.jp/1696/00039636/
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10
Experiment on a rectangular cross section scramjet combustor. Part 2: Effects of fuel injector geometry
Autor: Murakami, Atsuo, Komuro, Tomoyuki, Kudo, kenji
Publikováno v: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory. 1220:1-25
矩形断面スクラムジェット燃焼器において、混合効率と燃焼効率の向上をはかるため、ステップと燃料噴射孔の配置および燃料噴射孔下流の一定断面積部分(噴射器平行部)の長さを変え
Externí odkaz: https://explore.openaire.eu/search/publication?articleId=jairo_______::7150a3454207910c61f3cff329aca5b1
http://id.nii.ac.jp/1696/00041199/
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