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規格・テクニカルリポート類

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

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

Material type
規格・テクニカルリポート類
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
Capacity, size, etc.
-
NDC
-
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Note (General):

出版タイプ: NAIn the aerodynamic design of the National EXperimental Supersonic Transport (NEXST) program, a supersonic natural laminar flow (NLF) wing des...

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Digital

Material Type
規格・テクニカルリポート類
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
Publication, Distribution, etc.
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
Target Audience
一般
Note (General)
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
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)
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