@techreport{oai:jaxa.repo.nii.ac.jp:00006003,
 author = {橋本, 時忠 and 小室, 智幸 and 高橋, 政浩 and 佐藤, 和雄 and 伊藤, 勝宏 and Hashimoto, Tokitada and Komuro, Tomoyuki and Takahashi, Masahiro and Sato, Kazuo and Ito, Katsuhiro},
 month = {Nov},
 note = {In recent years, development of re-usable space transportation system is promoted. However, in order to realize it, development of the base technology is indispensable, particularly, aerodynamic heating and characteristics with strong real gas phenomena should be comprehended more precisely. Under such circumstances, acquisition of detailed experimental data like drag and heat transfer over hypersonic bodies is indispensable for the development of reliable space vehicles and thermal protection system (TPS), and also for the validation and progress of numerical estimation. In the present study, based on the numerical results a blunted double cone model (heat model) was designed and manufactured as the aerodynamic configuration design of re-entry capsules. The aim of this experiment is to obtain detailed data of heat flux and pressure distribution as well as the flow structures over the heat model. Coaxial thermocouples and pressure sensors are mounted at the frontal and base region thoroughly, and surface temperature and wall pressure are measured., 資料番号: AA0049500019, レポート番号: JAXA-SP-06-006},
 title = {再突入カプセルの高エンタルピ空力加熱試験},
 year = {2006}
}