@inproceedings{oai:jaxa.repo.nii.ac.jp:00004414,
 author = {丹羽, 史彰 and 櫻井, 鷹哉 and 久保田, 弘敏 and Niwa, Fumiaki and Sakurai, Takaya and Kubota, Hirotoshi},
 book = {宇宙航空研究開発機構特別資料: 第43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2011論文集, JAXA Special Publication: Proceedings of 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011},
 month = {Mar},
 note = {第43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2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京, 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8,  2011. Waseda University, International Conference Center), Tokyo Japan, For accomplishment of the future space plane, it is necessary to reduce both of aerodynamic drag and heating in the ascent flight especially reduction of aerodynamic drag is focused in this study. For the purpopose of such requirement, the concept of Directed Energy Air Spike (DEAS), which makes a virtual spike by applying a heat source in front of the vehicle with use of high power laser, is applied. The experiment with aerodynamics force measurement and flow visualization using a hypersonic wind tunnel of Mach 7 of Graduate School of the Frontier Science the University of Tokyo is conducted to study the effect of reduction of aerodynamic drag by DEAS, which aims to compare the results of the above mentioned effects by DEAS with actual aerospike., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065207042, レポート番号: JAXA-SP-11-015},
 pages = {243--246},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {仮想エアロスパイクに関する極超音速風洞実験},
 volume = {JAXA-SP-11-015},
 year = {2012}
}