Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project (Part 2)

• 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 (Part 2)
• 著者・編者: 吉田, 憲司; 上田, 良稲; Vermeersch, Olivier; Arnal, Daniel; Yoshida, Kenji; Ueda, Yoshine
• 著者標目: 吉田, 憲司; 上田, 良稲; Vermeersch, Olivier; Arnal, Daniel; Yoshida, Kenji; Ueda, Yoshine
• 出版事項: 宇宙航空研究開発機構(JAXA)
• 出版年月日等: 2013-03-29
• 出版年（W3CDTF）: 2013-03-29
• タイトル（掲載誌）: 宇宙航空研究開発機構研究開発報告
• 巻号年月日等（掲載誌）: JAXA-RR-12-009E
• 掲載巻: JAXA-RR-12-009E
• 掲載ページ: 1-142
• ISSN（掲載誌）: ISSN : 1349-1113
• 本文の言語コード: eng
• 件名標目: boundary layer transition; supersonic fl ow; linear stability analysis; e(N) method; natural laminar flow wing; flight test; wind tunnel test
• 対象利用者: 一般
• 一般注記: Stability analysis on a supersonic natural laminar flow (NLF) wing designed by JAXA was performed at both flight and wind tunnel test conditions as a joint research program between ONERA and JAXA. Both parties validated the NLF wing effect by confirming suppression of crossflow instability at design point, using an e(N) method with fixed β strategy proposed by ONERA. Although JAXA’s flight test vehicle and wind tunnel test model had almost same averaged roughness height of about 1micrometer, it was shown that surface roughness had little influence on measured transition location at both flight and wind tunnel test conditions. Furthermore, JAXA found that the pressure distribution measured in flight test did not completely coincide to the target pressure distribution (Cp (Target)) for the NLF wing design. It revealed that measured transition location at outer wing region was not delayed in flight test, compared with the transition location predicted with the Cp (Target) which had large gain to delay the transition. Influence of Reynolds number on transition location was also studied for the target pressure distribution Cp (Target). Consequently, chordwise transition location, (x/c)Tr., rapidly moves from mid-chord location to forward location (near leading edge) for increasing Reynolds numbers, according to the change of instability of boundary layer from Tollmien-Schlichting instability to crossflow instability.; 形態: カラー図版あり; Physical characteristics: Original contains color illustrations; 資料番号: AA0062081000; レポート番号: JAXA-RR-12-009E
• オンライン閲覧公開範囲: インターネット公開
• 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