@techreport{oai:jaxa.repo.nii.ac.jp:00006246,
 author = {加藤, 周徳 and 苅田, 丈士 and 富岡, 定毅 and 小林, 完 and 工藤, 賢司 and 村上, 淳郎 and Kato, Kanenori and Kanda, Takeshi and Tomioka, Sadatake and Kobayashi, Kan and Kudo, Kenji and Murakami, Atsuo},
 month = {Jan},
 note = {A rocket based combined cycle engine combustor was tested in scramjet-mode. The combustor model has two rockets in the combustor section. These rockets were used not only for thrust production, but also for fuel supply. The test facility consisted of an air supply section, a combustor section, a straight duct section, and a divergent duct section. Total pressure of the supplied air was 1 MPa, and the total temperature of the air was 2,400 K. In the tests, length of the straight duct section was changed to investigate its effects on the combustor performance. Two combustion patterns were observed for different lengths of straight duct. Pitot pressure and gas sampling were measured on the exit plane of the combustor model. Better combustion conditions were attained in the case of a longer duct., 資料番号: AA0049056015, レポート番号: JAXA-SP-05-010},
 title = {複合エンジン燃焼器におけるスクラムジェットモード試験},
 year = {2006}
}