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STOL実験機半截模型風洞試験(半截模型空力要素の特性)
https://jaxa.repo.nii.ac.jp/records/44991
https://jaxa.repo.nii.ac.jp/records/449916938d568-ba96-451f-b4bb-8f7a2c3e3e8d
名前 / ファイル | ライセンス | アクション |
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naltr00734.pdf (2.3 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 | STOL実験機半截模型風洞試験(半截模型空力要素の特性) | |||||
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_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 an Upper Surface Blown-Flap Half Model of the NAL STOL Research Aircraft | |||||
著者 |
高橋, 侔
× 高橋, 侔× 廣末, 健一× 宮本, 義人× 重見, 仁× 岩崎, 昭人× 玉置, 元昭× 織戸, 満紀雄× 森田, 義郎× TAKAHASHI, Hitoshi× HIROSUE, Kenichi× MIYAMOTO, Yoshito× SHIGEMI, Masashi× IWASAKI, Akihito× TAMAKI, Motoaki× ORITO, MAKIO× MORITA, YOSHIO |
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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 | ||||||
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 | ||||||
NASTADT | ||||||
著者所属 | ||||||
NASTADT | ||||||
著者所属 | ||||||
三菱重工業株式会社 | ||||||
著者所属(英) | ||||||
en | ||||||
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Mitsubishi Heavy Industries, Ltd. | ||||||
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報告 en : Technical Report of National Aerospace Laboratory TR-734 巻 734, p. 32, 発行日 1982-09 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | An investigation has been conducted to determine the aerodynamic characteristics of the aerodynamic elements of an 8% subsonic jet transport half model with an upper surface blowing flap system that would augment lift. Wind tunnel tests of leading edge and trailing edge high lift devices were conducted. After investigating those wind tunnel test data, some results were obtained. The set up angles of outer leading edge slats which were divided into three parts were all fixed at 40 degrees. It was determined that the USB flap was a hinged 40-70 type Forward-Main flap and that the inner leading edge had no device because any inner leading edge high lift devices were less effective in augmenting lift. Many data obtained in the wind tunnel tests were offered for the design of the NAL STOL Research Aircraft. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0734000 | |||||
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 TR-734 |