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菱形結合翼機の上翼舵面による直接横力制御力の低速風洞試験
https://jaxa.repo.nii.ac.jp/records/44228
https://jaxa.repo.nii.ac.jp/records/442283c8f551f-7bf7-453a-a5c3-81d3d3b4d76b
名前 / ファイル | ライセンス | アクション |
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naltm00645.pdf (2.2 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 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 菱形結合翼機の上翼舵面による直接横力制御力の低速風洞試験 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Low-speed wind tunnel; Joined-wing airplane; Direct side-force; Upper fin | |||||
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 | Low-speed Wind Tunnel Study of the Direct Side-Force Characteristics of a Joined-Wing Airplane with an Upper Fin | |||||
著者 |
藤田, 敏美
× 藤田, 敏美× 岩崎, 昭人× 藤枝, 郭俊× 滝澤, 直人× FUJITA, Toshimi× IWASAKI, Akihito× FUJIEDA, Hirotoshi× TAKIZAWA, NAOTO |
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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 | ||||||
元航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Aircraft Research group | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Aircraft Research group | ||||||
著者所属(英) | ||||||
en | ||||||
Advanced Aircraft Research group | ||||||
著者所属(英) | ||||||
en | ||||||
Formerly member of NAL | ||||||
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 645, p. 23, 発行日 1992-03 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 菱形結合翼機の直接横力制御における横力と操舵角余裕の増大のため上翼を採用した。風洞試験では,水平尾翼翼幅が主翼翼幅の60%の菱形結合翼機を用いた。上翼は後縁舵面を持ち,主翼翼幅の60%位置に垂直に設置した。試験で用いた4つの上翼は,異なる面積と縦横比を持ち,それらの二つはNACA0012翼型で,他の二つはEC1040翼型である。試験結果は,主翼前縁または主翼前方に張りだした上翼が直接横力制御に効果的であり,また大きな縦横比が横力を得るために有利であることが示された。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Low-speed wind tunnel tests were conducted on a diamond shaped joined-wing airplane model employing an upper fin system and having a wing span ratio (rear/front wing) of 0.60. The control surface was located at the trailing edge portion of the upper fin which are vertically situated at 60% spanwise location of the front wing. Four upper fins were tested, each having a different wing area and aspect ratio. Two fins used the NACA0012 wing section and two the EC 1040 wing section. Results indicate that an upper fin installed at the front wing leading edge or an over hanging upper fin are most effective for obtain direct side-force. In addition, the larger aspect ratio of these fin configurations was found to be superior to the gain of the side-force. | |||||
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: NALTM0645000 | |||||
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-645 |