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超音速燃焼飛行試験に用いる燃焼器流路形状の検討
https://jaxa.repo.nii.ac.jp/records/46354
https://jaxa.repo.nii.ac.jp/records/463541619a478-8bb1-4dc7-8d1d-dafcc73c532e
名前 / ファイル | ライセンス | アクション |
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AA1930011013.pdf (2.3 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2020-02-04 | |||||
タイトル | ||||||
タイトル | 超音速燃焼飛行試験に用いる燃焼器流路形状の検討 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Flow-path Design of a Combustor Model for a Supersonic-combustion Flight Experiment | |||||
著者 |
髙橋, 政浩
× 髙橋, 政浩× 富岡, 定毅× Takahashi, Masahiro× Tomioka, Sadatake |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構(JAXA) | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集 en : JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium 巻 JAXA-SP-19-007, p. 157-164, 発行日 2020-02-04 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A flight-ground test comparison program is undergoing at JAXA to reveal so-called facility effects on hypersonic aerodynamics and combustion phenomena. The flight test vehicle will mount a combustor duct along its centerline, with so-called alligator type inlet with side-spillage to attain good starting characteristics. In the present paper, parametric study on flow-path design of the combustor model was conducted by CFD to examine influences of the geometry parameters, such as configurations of fuel injector holes and geometry of a flame-holding cavity, on combustion characteristics and to settle the design guideline which could enhance so-called vitiation effects on combustion. A two-staged fuel injection scheme was adopted for the combustor model and the first-stage and second-stage injection holes were installed at upstream and downstream of the flame-holding cavity, respectively. The results showed that a distance between the first-stage injection hole and the flame-holding cavity as well as the number of the injector holes at each stage would have strong influence on the combustor flow-field and its characteristics while the depth of the flame-holding cavity would have little influence. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSNONLINE | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 2433-2232 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1930011013 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-19-007 |