STOL実験機半截模型風洞試験(半截模型空力要素の特性)

• 資料種別: 文書・図像類
• 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)
• 著者・編者: 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
• 著者標目: 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
• 出版事項: 航空宇宙技術研究所
• 出版年月日等: 1982-09
• 出版年（W3CDTF）: 1982-09
• 並列タイトル等: Wind Tunnel Investigation of an Upper Surface Blown-Flap Half Model of the NAL STOL Research Aircraft
• タイトル（掲載誌）: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-734
• 巻号年月日等（掲載誌）: 734
• 掲載巻: 734
• 掲載ページ: 32-
• ISSN（掲載誌）: ISSN : 0389-4010
• 本文の言語コード: jpn
• 対象利用者: 一般
• 一般注記: 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.; 資料番号: NALTR0734000; レポート番号: NAL TR-734
• 一次資料へのリンクURL: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44991&item_no=1&attribute_id=31&file_no=1
• オンライン閲覧公開範囲: 限定公開
• 連携機関・データベース: 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• 提供元機関・データベース: 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ