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環状スリットノズルからの二次空気によるジェット騒音低減の試み
https://jaxa.repo.nii.ac.jp/records/3628
https://jaxa.repo.nii.ac.jp/records/3628390f1942-694a-4c5b-b5c0-ccf044b8dde4
名前 / ファイル | ライセンス | アクション |
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AA1630005003.pdf (695.0 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2016-04-21 | |||||
タイトル | ||||||
タイトル | 環状スリットノズルからの二次空気によるジェット騒音低減の試み | |||||
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 | Jet Noise Reduction Using Secondary Air from Annular Slit Nozzle | |||||
著者 |
佐藤, 寛太
× 佐藤, 寛太× 沢田, 恭兵× 生沼, 秀司× 石井, 達哉× 金子, 成彦× Sato, Kanta× Sawada, Kyohei× Oinuma, Hideshi× Ishii, Tatsuya× Kaneko, Shigehiko |
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著者所属 | ||||||
東京大学 | ||||||
著者所属 | ||||||
東京大学 | ||||||
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 | ||||||
東京大学 | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
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47回流体力学講演会/第33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 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium 巻 JAXA-SP-15-013, p. 29-33, 発行日 2016-03-08 |
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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47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 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 | 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | It is known that the microjet blowing secondary air to the jet shear layer is effective in reducing jet mixing noise. One of the considerations for the microjet is a nozzle shape for injecting the secondary air. In the previous studies, the flow rate and the arrangements of microjet nozzles under cold jet were investigated. Considering the application of the microjet to the actual engine, however, it is necessary to grasp the acoustic characteristics under heated jet. In this paper, we applied the microjet nozzle of annular slit shape to the model-scale turbojet engine with changing the split number and cross sectional area of microjet and evaluated the far-field noise reduction effect. | |||||
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 | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1630005003 | |||||
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-15-013 |