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膨張領域を持つwaveriderの数値解析および簡易空力評価法との比較
https://jaxa.repo.nii.ac.jp/records/3500
https://jaxa.repo.nii.ac.jp/records/3500de849c1b-7c8a-4976-ba20-7bb6ca1971cf
名前 / ファイル | ライセンス | アクション |
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AA1630031025.pdf (2.1 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2017-01-13 | |||||
タイトル | ||||||
タイトル | 膨張領域を持つwaveriderの数値解析および簡易空力評価法との比較 | |||||
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 | Comparisons between CFD and panel methods for a waverider with expansion area | |||||
著者 |
森田, 直人
× 森田, 直人× 土屋, 武司× Morita, Naoto× Tsuchiya, Takeshi |
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著者所属 | ||||||
東京大学 | ||||||
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 | ||||||
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48回流体力学講演会/第34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 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium 巻 JAXA-SP-16-007, p. 183-188, 発行日 2016-12-27 |
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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48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川 | |||||
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 | 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | For the realization of the space plane, the high accuracy of aerodynamic estimation and system analyses are needed. In our past studies, we have obtained an optimal configuration of waverider-winged spaceplanes by using simultaneous trajectory and design optimization. As a further research of the result, we conducted CFD analyses on the obtained spaceplane. Our studies compared results of FaSTAR, which is developed by Japan Aerospace Exploration Agency, and panel methods. We used PANAIR which is panel method with high accuracy and HYPER which is solver of modified newtonian as the panel methods. When we compared between the results of the CFD and the panel methods, the CL and CD values are similar to the both results. However in almost all of the mach numbers, the panel methods estimated smaller Cm values than the CFD code. This is because panel method cannot consider interference of shock wave between body and wing. In addition, the effectiveness of V-tail was estimated in smaller value than CFD's results. Then, we should pay attention to the interference between wing and body when we consider problems using panel methods or establish more reliably combinations of panel methods and CFDs to do more accurate aerodynamic analyses about the space planes' optimization. | |||||
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: AA1630031025 | |||||
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-16-007 |