航空宇宙技術研究所
航空宇宙技術研究所
航空宇宙技術研究所
航空宇宙技術研究所
航空宇宙技術研究所
ONERA Aerodynamics and Energetics Models Dept.
ONERA Aerodynamics and Energetics Models Dept.
ONERA Aerodynamics and Energetics Models Dept.
著者所属（英）
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
National Aerospace Laboratory
Office National d'Etudes et de Recherches Aerospatiales Aerodynamics and Energetics Models Department
Office National d'Etudes et de Recherches Aerospatiales Aerodynamics and Energetics Models Department
Office National d'Etudes et de Recherches Aerospatiales Aerodynamics and Energetics Models Department
出版者
宇宙航空研究開発機構
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料
雑誌名(英)
JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)
SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20011203-20011205 Tokyo Japan
抄録（英）
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 NAL-ONERA cooperative research project started in April 2000, because ONERA had great ability of analyzing transition phenomena and NAL 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, almost good cross validation of both ONERA's and NAL's e(sup N) codes was obtained. Then, there was also high correlation between the S2MA wind tunnel test results and both laboratories' predictions under the assumption of a critical transition N value of 6. Moreover, about 40 percent chordwise region was estimated to be laminar at flight condition by NAL's code. In addition, a risk of transition due to attachment-line contamination was predicted at inner wing, using the well-known Poll's criterion.
Boundary layer transition analysis on NEXST-1 airplane: NAL-ONERA cooperative research project
63609064.pdf
(1.26MB)
