@article{oai:nagoya.repo.nii.ac.jp:00012004,
 author = {西野, 敦洋 and NISHINO, Atsuhiro and 石川, 尊史 and ISHIKAWA, Takahumi and 中村, 佳朗 and NAKAMURA, Yoshiaki},
 issue = {621},
 journal = {日本航空宇宙学会論文集},
 month = {Oct},
 note = {As future space vehicles, Reusable Launch Vehicle (RLV) needs to be developed, where there are two kinds of RLV: Single Stage To Orbit (SSTO) and Two Stage To Orbit (TSTO). In the latter case, the shock/shock interaction and shock/boundary layer interaction play a key role. In the present study, we focus on the supersonic flow field with aerodynamic interaction between a delta wing and a hemisphere-cylinder, which imitate a TSTO, where the clearance, h, between the delta wing and hemisphere-cylinder is a key parameter. As a result, complicated flow patterns were made clear, including separation bubbles.},
 pages = {446--451},
 title = {超音速におけるデルタ翼・半球円柱間の空力干渉流れ場},
 volume = {53},
 year = {2005}
}