@inproceedings{oai:jaxa.repo.nii.ac.jp:00006523,
 author = {山本, 一臣 and 高木, 亮治 and 竹中, 啓三 and 伊藤, 良三 and 田中, 健太郎 and Yamamoto, Kazuomi and Takaki, Ryoji and Takenaka, Keizo and Ito, Ryozo and Tanaka, Kentaro},
 book = {宇宙航空研究開発機構特別資料: 第70回風洞研究会議論文集, JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 70th Meeting},
 month = {Feb},
 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: AA0048062003, レポート番号: JAXA-SP-04-009},
 pages = {16--21},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {小型超音速ロケット実験機の音速近傍風洞試験における壁干渉の影響},
 volume = {JAXA-SP-04-009},
 year = {2005}
}