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

Material type: 文書・図像類

Author: 吉田, 憲司ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2010-03-31

Material Format: Digital

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Note (General)：: In the aerodynamic design of the National EXperimental Supersonic Transport (NEXST) program, a supersonic natural laminar flow (NLF) wing design conce...

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Material Type: 文書・図像類
Title: Experimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project
Author/Editor: 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
Author Heading: 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
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2010-03-31
Publication Date (W3CDTF): 2010-03-31
Periodical title: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
No. or year of volume/issue: JAXA-RR-08-007E
Volume: JAXA-RR-08-007E
Pages: 1-104
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: eng
Subject Heading: boundary layer transition, supersonic flow, linear stability analysis, e(Sup N) method, natural laminar flow, transition measurement
Target Audience: 一般
Note (General): 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
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2109&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2109&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
Data Provider (Database): 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
Original Data Provider (Database): 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