@inproceedings{oai:jaxa.repo.nii.ac.jp:00038245,
 author = {山本, 行光 and 穂積, 弘一 and 戸塚, 亜希子 and 金田, 誠 and 保阪, 陽子 and 上敷領, 早苗 and Yamamoto, Yukimitsu and Hozumi, Koichi and Totsuka, Akiko and Kaneda, Makoto and Hosaka, Yoko and Kamishikiryo, Sanae},
 book = {航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002},
 month = {Mar},
 note = {Hypersonic aerodynamic heating problem has been investigated for the shock-shock interactions of two hemi-sphere cylinder problem for future TSTO space transport systems. Two hemisphere models with a diameter of 3 cm and 6 cm are placed parallel or with the inclined angles and hypersonic wind tunnel tests have been made by NAL Mach 10 HWT. Severe local peak heating is generated on the small hemisphere nose by strong shock-shock interactions of Type 3 at the inclined angle of 15 deg. In the parallel setting cases at high angles of attack. Type 1 and Type 2 shock interaction patterns are observed. CFD computations can predict local peak heating accurately in the interaction area and the structure of shock-shock, shock-boundary layer interaction can be resolved in detail., 資料番号: AA0045948024, レポート番号: NAL SP-57},
 pages = {136--139},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {将来型TSTO宇宙輸送システムのための2体問題衝撃波干渉の極超音速風洞検証},
 volume = {57},
 year = {2003}
}