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Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles GOTO, Keisuke 後藤, 啓介 ゴトウ, ケイスケ NISHIMURA, Junpei 西村, 純平 ニシムラ, ジュンペイ KAWASAKI, Akira 川崎, 央 カワサキ, アキラ MATSUOKA, Ken 松岡, 健 マツオカ, ケン 笠原, 次郎 KASAHARA, Jiro カサハラ, ジロウ 松尾, 亜紀子 MATSUO, Akiko マツオ, アキコ FUNAKI, Ikkoh 船木, 一幸 フナキ, イッコウ 中田, 大将 NAKATA, Daisuke ナカタ, ダイスケ 内海, 政春 ウチウミ, マサハル UCHIUMI, Masaharu 東野, 和幸 ヒガシノ, カズユキ HIGASHINO, Kazuyuki 538 application/pdf Geometric throats are commonly applied to rocket combustors to increase pressure and specific impulse. This paper presents the results from thrust measurements of an ethylene/gas-oxygen rotating detonation engine with various throat geometries in a vacuum chamber to simulate varied backpressure conditions in a range of 1.1–104 kPa. For the throatless case, the detonation channel area was regarded to be equivalent the throat area, and three throat-contraction ratios were tested: 1, 2.5, and 8. Results revealed that combustor pressure was approximately proportional to equivalent throat mass flux for all test cases. Specific impulse was measured for a wide range of pressure ratios, defined as the ratio of the combustor pressure to the backpressure in the vacuum chamber. The rotating detonation engine could achieve almost the same level of optimum specific impulse for each backpressure, whether or not flow was squeezed by a geometric throat. In addition, heat-flux measurements using heat-resistant material are summarized. Temporally and spatially averaged heat flux in the engine were roughly proportional to channel mass flux. Heat-resistant material wall compatibility with two injector shapes of doublet and triplet injection is also discussed. journal article American Institute of Aeronautics and Astronautics (AIAA) 2019-01 AM application/pdf Journal of Propulsion and Power 1 35 213 223 0748-4658 https://muroran-it.repo.nii.ac.jp/record/9969/files/JPP_35_1_213_223.pdf http://hdl.handle.net/10258/00009917 https://muroran-it.repo.nii.ac.jp/records/9969 eng 10.2514/1.B37196 AIAA Aerospace Research Central https://arc.aiaa.org/ © 2019 American Institute of Aeronautics and Astronautics (AIAA) open access