@inproceedings{oai:jaxa.repo.nii.ac.jp:00006643,
 author = {山本, 一臣 and 竹中, 啓三 and 高木, 亮治 and 伊藤, 良三 and 田中, 健太郎 and Yamamoto, Kazuomi and Takenaka, Keizo and Takaki, Ryoji and Ito, Ryozo and Tanaka, Kentaro},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003},
 month = {Mar},
 note = {Development of a next-generation airplane cruising near sonic speed received considerable attention in 2002. It requires a better understanding of corresponding aerodynamic characteristics and CFD validity. As a part of the collaboration between NAL and MHI on transonic wind tunnel tests and CFD computations using NEXST-1 supersonic transport model, the effect of wall interference in NAL 2 m x 2 m transonic wind tunnel at near sonic speed condition was investigated with CFD based on Reynolds-averaged Navier-Stokes equations. The results showed considerable drag reduction (dip) at Mach number just below the drag divergence Mach number due to the interaction of wall and sting support., 資料番号: AA0047427042, レポート番号: JAXA-SP-03-002},
 pages = {238--243},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {NEXST-1音速近傍風洞試験における壁干渉の影響},
 volume = {JAXA-SP-03-002},
 year = {2004}
}