@inproceedings{oai:jaxa.repo.nii.ac.jp:00005609,
 author = {金森, 正史 and 今村, 宰 and 鈴木, 宏二郎 and Kanamori, Masashi and Imamura, Osamu and Suzuki, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集, JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007},
 month = {Feb},
 note = {We numerically analyze supersonic flows around a delta wing with bent wing tip. The results show that the lift and drag forces decrease with the increase in the bending angle. But the local augmentation is observed around the hinge line of bending in the spanwise distribution. On the other hand, the lift-to-drag ratio keeps almost the same value independent of the bending angle. This phenomenon is significantly related to the interaction between shock waves generated at the wing root and tip. The mechanism of lift augmentation is explained as the 'compression lift' effect due to this shock-shock interaction., 資料番号: AA0063742003, レポート番号: JAXA-SP-07-016},
 pages = {17--21},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {圧縮揚力による超音速デルタ翼の揚抗比増加に関する数値解析},
 volume = {JAXA-SP-07-016},
 year = {2008}
}