JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
64668000.pdf18.84 MB
titleExperimental and Numerical Research on Boundary Layer Transition Analysis at Supersonic Speed: JAXA-ONERA cooperative research project
Author(jpn)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
Author(eng)Yoshida, Kenji; Sugiura, Hiroki; Ueda, Yoshine; Ishikawa, Hiroaki; Tokugawa, Naoko; Atobe, Takashi; Takagi, Shohei; Arnal, Daniel; Archambaud, Jean-Pierre; Seraudie, Alain
Author Affiliation(jpn)宇宙航空研究開発機構航空プログラムグループ超音速機チーム; 宇宙航空研究開発機構研究開発本部流体グループ; 宇宙航空研究開発機構航空プログラムグループ超音速機チーム; 宇宙航空研究開発機構航空プログラムグループ超音速機チーム; 宇宙航空研究開発機構航空プログラムグループ超音速機チーム; 宇宙航空研究開発機構研究開発本部流体グループ; 宇宙航空研究開発機構研究開発本部流体グループ; フランス航空宇宙研究所空力/エネルギーモデル部; フランス航空宇宙研究所空力/エネルギーモデル部; フランス航空宇宙研究所空力/エネルギーモデル部
Author Affiliation(eng)Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Fluid Dynamics Group, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency (JAXA); Fluid Dynamics Group, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Fluid Dynamics Group, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Department of Aerodynamics and Energetics Modeling, ONERA/DMAE; Department of Aerodynamics and Energetics Modeling, ONERA/DMAE; Department of Aerodynamics and Energetics Modeling, ONERA/DMAE
Issue Date2010-03-31
Publisher宇宙航空研究開発機構
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発報告
JAXA reseach and development report
VolumeJAXA-RR-08-007E
Start page1
End page104
Publication date2010-03-31
Languageeng
AbstractIn 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.
DescriptionOriginal contains color illustrations
形態: カラー図版あり
Keywordsboundary layer transition, supersonic flow, linear stability analysis, e(Sup N) method, natural laminar flow, transition measurement
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
NCIDAA1192675X
SHI-NOAA0064668000
Report NoJAXA-RR-08-007E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/17014


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.