@inproceedings{oai:jaxa.repo.nii.ac.jp:00005788,
 author = {真保, 雄一 and 吉田, 憲司 and Shinbo, Yuichi and Yoshida, Kenji},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)},
 month = {Mar},
 note = {SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20011203-20011205 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20011203-20011205 Tokyo Japan, The high-speed wind tunnel tests of the NEXST-1 (National EXperimental Supersonic Transport-1) were conducted in 1999 at the 1 m x 1 m Supersonic Wind Tunnel of NAL. The main objectives of the tests were to confirm the CFD (Computational Fluid Dynamics)-and-inverse-method-based supersonic natural laminar flow wing design, to collect wind tunnel data to be correlated with CFD and flight test data of the NEXST-1 and to supply data for validation and further development of the CFD tools, other than to collect aerodynamic data to be used in the detailed system design phase of the NEXST-1. At M = 2.0 where the data were presented for the workshop, the force test data showed very smooth longitudinal characteristics. The pressure test results proved that the flat-type pressure distribution was achieved on the upper surface as was intended in the wing design, and the data also showed good repeatability and good agreement with ones of a larger model tested in ONERA., 資料番号: AA0063609057, レポート番号: JAXA-SP-06-029E},
 pages = {464--467},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Description of the wind tunnel test data of the NEXST-1},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}