@inproceedings{oai:jaxa.repo.nii.ac.jp:00005762,
 author = {吉田, 憲司 and 岩宮, 敏幸 and 上田, 良稲 and 石川, 敬掲 and Yoshida, Kenji and Iwamiya, Toshiyuki and Ueda, Yoshine and Ishikawa, Hiroaki},
 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 20000117-20000119 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan, Boundary layer transition characteristics of the scaled supersonic experimental airplane was numerically analyzed to confirm its Natural Laminar Flow (NLF) wing design. Using conventional incompressible and newly developed compressible transition prediction codes based on an e(sup N) method, the NLF characteristics were well confirmed though the following results. (1) The step function type target pressure distribution applied in the NLF wing design was found to be optimum (2) Comparing the transition N value estimated by the compressible code with experimental results obtained by NASA, wide laminar region of the NLF wing was expected. (3) Laminar boundary layer profiles estimated by a Navier-Stokes code led to smaller N value than one by the compressible boundary layer code. (4) No transition due to attachment-line contamination was predicted., 資料番号: AA0063609031, レポート番号: JAXA-SP-06-029E},
 pages = {280--285},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Boundary layer transition analysis of the scaled supersonic experimental airplane},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}