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Low-Boom and Low-Drag Design of Small Supersonic Transport Considering Propulsion Airframe Integration
https://jaxa.repo.nii.ac.jp/records/2442
https://jaxa.repo.nii.ac.jp/records/2442fd8c4717-5383-4fe1-b5b4-b7391205533e
名前 / ファイル | ライセンス | アクション |
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AA1830004000.pdf (48.0 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2018-10-03 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Low-Boom and Low-Drag Design of Small Supersonic Transport Considering Propulsion Airframe Integration | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Supersonics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Low-boom | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Propulsion airframe integration | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
著者 |
上野, 篤史
× 上野, 篤史× 牧野, 好和× Ueno, Atsushi× Makino, Yoshikazu |
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著者所属 | ||||||
宇宙航空研究開発機構航空技術部門航空システム研究ユニット(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構航空技術部門航空システム研究ユニット(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Aviation Systems Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Aviation Systems Research Unit, Aeronautical Technology Directorate, 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研究開発資料 en : JAXA Research and Development Memorandum 巻 JAXA-RM-18-001E, p. 1-14, 発行日 2018-10-03 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Japan Aerospace Exploration Agency (JAXA) has conducted a low-boom and low-drag design considering propulsion airframe integration for a 50-seat-class supersonic transport. In this study, three technical targets in terms of airport noise, lift-to-drag ratio, and sonic boom were defined. Design results complying with three technical targets are summarized in this paper. First, engine specifications are optimized to comply with ICAO noise standards. In this optimization, only the engine (jet) noise is considered, and the engine exhaust velocity that has strong impact on jet noise is constrained. The objective function to be maximized is the range performance. Then, the engine nacelle is designed based on the optimized engine specifications and is integrated with the low-boom-designed airframe considering range performance and sonic boom loudness. Finally, technical targets on lift-to-drag ratio and sonic boom are validated by the Navier-Stokes analysis and wind tunnel tests. | |||||
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 | 2433-2224 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1830004000 | |||||
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-RM-18-001E |