@techreport{oai:jaxa.repo.nii.ac.jp:00044827,
 author = {鎮西, 信夫 and 升谷, 五郎 and 石井, 進一 and 工藤, 賢司 and 村上, 淳郎 and 小室, 智幸 and CHINZEI, NOBUO and MASUYA, Goro and ISHII, Shinichi and KUDO, Kenji and MURAKAMI, Atsuo and KOMURO, Tomoyuki},
 month = {Apr},
 note = {Subsonic(downstream choking) mode combustion in cylindrical secondary combustors of air breathing rockets was investigated. Two different types of experimental apparaturs(A and B) were used. Apparatus A inhaled atmospheric air using ejector exhaust system, so that the air stagnation pressure was kept at a constant one atmosphere. In apparatus B, compressed air was supplied to the secondary combustor, in order to keep air flow rate constant. Axial wall pressure distribution, air flow rate(in apparatus A) or air stagnation pressure(in apparatus B), and the radial distribution of Pitot pressure and temperature(only in apparatus A) at the exit of the secondary combustor were measured. These experimental results were compared with ideal conditions at the exit and the air inlet of the secondary combustor, which were then calculated on the assumption of the complete mixing and burning primary rocket exhaust and air stream. A one-dimensional analysis with the measured wall pressure distribution made it possible to calculate axial distribution of other properties such as Mach number, stagnation temperature, and so on. From the stagnation temperature distribution in a sufficiently long secondary combustor, we determined “effective flame length”lf and used it as a measure of necessary combustor length. The performances of the secondary combustors were well correlated to the non-dimensional combustor length, L/lf., 資料番号: NALTR0573000, レポート番号: NAL TR-573},
 title = {空気吸込式ロケットの研究(Ⅰ)-亜音速モード円筒型二次燃焼器の圧力分布と燃焼性能-},
 year = {1979}
}