Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project

• 資料種別: 規格・テクニカルリポート類
• タイトル: Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project
• 著者・編者: 吉田, 憲司; 杉浦, 裕樹; 上田, 良稲; 石川, 敬掲; 徳川, 直子; 跡部, 隆; 高木, 正平; Yoshida, Kenji; Sugiura, Hiroki; Ueda, Yoshine; Ishikawa, Hiroaki; Tokugawa, Naoko; Atobe, Takashi; Takagi, Shohei; Arnal, Daniel; Archambaud, Jean-Pierre; Seraudie, Alain
• 著者標目: 吉田, 憲司; 杉浦, 裕樹; 上田, 良稲; 石川, 敬掲; 徳川, 直子; 跡部, 隆; 高木, 正平; Yoshida, Kenji; Sugiura, Hiroki; Ueda, Yoshine; Ishikawa, Hiroaki; Tokugawa, Naoko; Atobe, Takashi; Takagi, Shohei; Arnal, Daniel; Archambaud, Jean-Pierre; Seraudie, Alain
• 出版事項: 宇宙航空研究開発機構
• 出版年月日等: 2010-03-31
• 出版年（W3CDTF）: 2010-03-31
• タイトル（掲載誌）: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
• 巻号年月日等（掲載誌）: JAXA-RR-08-007E
• 掲載巻: JAXA-RR-08-007E
• 掲載ページ: 1-104
• ISSN（掲載誌）: ISSN : 1349-1113
• 本文の言語コード: eng
• 件名標目: boundary layer transition, supersonic flow, linear stability analysis, e(Sup N) method, natural laminar flow, transition measurement
• 対象利用者: 一般
• 一般注記: 出版タイプ： NA; In the aerodynamic design of the National EXperimental Supersonic Transport (NEXST) program, a supersonic natural laminar flow (NLF) wing design concept was originally developed. Before the flight test of the NEXST-1 airplane, more detailed transition analysis should be performed in order to validate the NLF wing effect. Therefore, the JAXA-ONERA cooperative research project started in April 2000, because ONERA had great ability of analyzing transition phenomena and JAXA had some experimental transition data in supersonic flow. In the transition analysis on the sharp cone with a half angle of 5 degrees, the nose cone, and the NLF wing of the NEXST-1 airplane, good cross validation of both ONERA's and JAXA 's e(N) codes was obtained. There was also high correlation between the experimental results in ONERA's continuous circuit-flow type supersonic wind tunnel and both laboratories' predictions under the assumption of a critical transition N value of 6. In addition, a risk of transition due to attachment-line contamination was predicted at inner wing, using the well-known Poll's criterion.; 形態: カラー図版あり; Physical characteristics: Original contains color illustrations; 資料番号: AA0064668000; レポート番号: JAXA-RR-08-007E
• 掲載誌（NCID）: AA1192675X; https://ci.nii.ac.jp/ncid/AA1192675X
• 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