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CAD設計によるUSB-STOL機半裁模型の風洞試験 第2報
https://jaxa.repo.nii.ac.jp/records/41133
https://jaxa.repo.nii.ac.jp/records/41133d6023527-7dc0-4d34-9df8-ba0d5460d493
名前 / ファイル | ライセンス | アクション |
---|---|---|
naltm00670.pdf (3.0 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 | CAD設計によるUSB-STOL機半裁模型の風洞試験 第2報 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CAD | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | コンピューター支援設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | USB | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼上面吹き出し | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | STOL | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 短距離離着陸 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 半裁模型 | |||||
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 | 空力形状 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ターボジェット機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 主翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 機体重量 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 亜音速流 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CAD | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computer aided design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | USB | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | upper surface blowing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | STOL | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | short take off and landing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | half span model | |||||
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 | aerodynamic form | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | turbojet engine aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | main wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | airframe weight | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | subsonic flow | |||||
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 | Wind tunnel investigation of a USB-STOL transport semi-span model, part 2 | |||||
著者 |
高橋, ひとし
× 高橋, ひとし× 奥山, 政広× 藤枝, 郭俊× 藤田, 敏美× 岩崎, 昭人× Takahashi, Hitoshi× Okuyama, Masahiro× Fujieda, Hirotoshi× Fujita, Toshimi× Iwasaki, Akihito |
|||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属 | ||||||
航空宇宙技術研究所 新型航空機研究グループ | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory Advanced Aircraft Research Group | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所資料 en : Technical Memorandum of National Aerospace Laboratory 巻 670, p. 1-58, 発行日 1994-11 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | STOL実験機「飛鳥」は国産中型輸送機C-1からUSB方式STOL機に改造されたが、その設計において、かなりの制約が設けられている。そのため、STOL機として必ずしも最適な空力形状をしているわけではない。そこでSTOL実験機の開発過程で得られた成果を反映して整備されたSTOL-CAD(コンピューター支援設計)プログラムを用いて、150人乗り程度のターボ・ジェット機に適すると思われる主翼を設計し、本主翼を有する半截模型(CAD模型)を製作し、STOL機を構成する空力要素の最適形状を求めるため、風洞試験を実施した。本資料はこれら風洞試験結果の第2報であり、本結果において、CAD模型は「飛鳥」模型に比べて、大幅な空力特性の改善、機体重量の軽減の可能性を得ることができた。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The Quiet Short Take-Off and Landing (QSTOL) Experimental Aircraft 'ASKA' has been researched and developed by the National Aerospace Laboratory (NAL). The 'ASKA' was based upon the airframe of the home produced C-1 tactical transport which was modified into the Upper Surface Blowing (USB) -powered high-lift STOL aircraft. The wing configuration, however, was not changed. Therefore, this Experimental Aircraft does not always have the optimum configuration of a USB-type aircraft. So the improvement of the aerodynamic characteristics of the STOL Aircraft was tried. This paper describes the investigations which have been conducted to improve the aerodynamic characteristics of a subsonic jet transport semi-span model with an Upper Surface Blown Flap system which has been newly designed using the NAL STOL-CAD (computer Aided Design) program. The model had an 8.2 deg swept wing of aspect ratio 10.0 and four turbofan engines with short USB nozzles. The tests were conducted in the NAL 2 x 2 m Gust Wind Tunnel with closed section and results were obtained for several flap and slat deflections at jet momentum coefficients from 0 to 1.85. Compared with the aerodynamic characteristics of the 'ASKA' model, it was determined that the airframe weight can be reduced and the aerodynamic characteristics can be improved significantly. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0452-2982 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00314334 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0004154000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TM-670 |