WEKO3
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極超音速機のマッハ5空力特性試験
https://jaxa.repo.nii.ac.jp/records/2127
https://jaxa.repo.nii.ac.jp/records/212762da5a89-4a1f-481c-b63c-dc28835936d7
名前 / ファイル | ライセンス | アクション |
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63912000.pdf (1.5 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 極超音速機のマッハ5空力特性試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力係数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 極超音速機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 風洞模型 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 迎角 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 剥離流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層剥離 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エンジン装着形状 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic coefficient | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypersonic aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wind tunnel model | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | angle of attack | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | separated flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer separation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | engine-installed configuration | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Mach 5 wind tunnel test of hypersonic airplane | |||||
著者 |
田口, 秀之
× 田口, 秀之× 藤田, 和央× 進藤, 重美× 津田, 尚一× 平林, 則明× 小山, 忠勇× 伊藤, 良三× Taguchi, Hideyuki× Fujita, Kazuhisa× Shindo, Shigemi× Tsuda, Shoichi× Hirabayashi, Noriaki× Koyama, Tadao× Ito, Ryozo |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ 超音速機チーム | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 空気力学研究グループ | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 航空プログラムグループ 超音速機チーム | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 風洞技術開発センター | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 情報・計算工学センター | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Aerodynamics Research Group, Institute of Aerospace Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency JAXA's Engineering Digital Innovation Center | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
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報告 en : JAXA Research and Development Report 巻 JAXA-RR-07-047, 発行日 2008-02-29 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 極超音速実験機のマッハ5空力特性を0.5mJAXA極超音速風洞で取得した。機体模型の6分力計測を行うとともに、実験機の飛行環境を摸擬したCFD(Computational Fluid Dynamics)解析を実施した。結果として、迎角に対する空力係数の変化は風洞試験とCFDで概ね一致した。風洞試験においては、機体上面に大規模な剥離域が観察された。風洞試験とCFDにおける空力係数の違いは、剥離域の違いの影響と推測された。エンジンを装着した形状では、法線力係数と軸力係数が上昇した。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Mach 5 aerodynamic coefficients for a hypersonic experimental airplane are examined at JAXA 0.5 m hypersonic wind tunnel. Six DOF (Degree Of Freedom) forces for the model are measured and evaluated. CFD (Computational Fluid Dynamics) analyses for the same airframe are performed simulating real flight condition for the experimental airplane. As a result, variations of aerodynamic coefficients on angle of attack for both wind tunnel test and CFD analysis are consistent in general. Large separation region is observed on the upper surface of the body at the wind tunnel test. It is presumed that the difference of aerodynamic coefficients has occurred by the difference in flow separation between the wind tunnel test and CFD. Lateral force coefficient and axial force coefficient are raised with engine installed configuration. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-1113 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA1192675X | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063912000 | |||||
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-RR-07-047 |