@techreport{oai:jaxa.repo.nii.ac.jp:00045014,
 author = {升谷, 五郎 and 鎮西, 信夫 and 工藤, 賢司 and 村上, 淳郎 and 小室, 智幸 and 石井, 進一 and MASUYA, Goro and CHINZEI, NOBUO and KUDO, Kenji and MURAKAMI, Atsuo and KOMURO, Tomoyuki and ISHII, Shinichi},
 month = {Apr},
 note = {An experimental study was made on supersonic mode combustors of an air breathing rocket engine. Supersonic streams of room-temperature air and hot fuel-rich rocket exhaust were coaxially mixed and burned in a conically diverging duct of 2deg half-angle. The effect of air inlet Mach number and excess air ratio was investigated. Axial wall pressure distribution was measured to calculate one dimensional change of Mach number and stagnation temperature. Calculated results showed that supersonic combustion occurred in the duct. At the exit of the duct, gas sampling and Pitot pressure measurement was made, from which radial distributions of various properties were deduced. The distribution of mass fraction of elements from rocket exhaust showed poor mixing performance in the supersonic mode combustors compared with the previously investigated cylindrical subsonic mode combustors. Secondary combustion efficiency correlated well with the centerline mixing parameter, but not with Annushkin’s non-dimensional combustor length. No major effect of air inlet Mach number or excess air ratio was seen within the range of conditions under which the experiment was conducted., 資料番号: NALTR0756000, レポート番号: NAL TR-756},
 title = {空気吸込ロケットの研究(III)-超音速モード燃焼器-},
 year = {1983}
}