@article{oai:muroran-it.repo.nii.ac.jp:00009969,
 author = {GOTO, Keisuke and 後藤, 啓介 and NISHIMURA, Junpei and 西村, 純平 and KAWASAKI, Akira and 川崎, 央 and MATSUOKA, Ken and 松岡, 健 and 笠原,  次郎 and KASAHARA, Jiro and 松尾, 亜紀子 and MATSUO, Akiko and FUNAKI, Ikkoh and 船木, 一幸 and 中田, 大将 and NAKATA, Daisuke and 内海, 政春 and UCHIUMI, Masaharu and 東野,  和幸 and HIGASHINO, Kazuyuki},
 issue = {1},
 journal = {Journal of Propulsion and Power},
 month = {Jan},
 note = {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.},
 pages = {213--223},
 title = {Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles},
 volume = {35},
 year = {2019},
 yomi = {ゴトウ, ケイスケ and ニシムラ, ジュンペイ and カワサキ, アキラ and マツオカ, ケン and カサハラ, ジロウ and マツオ, アキコ and フナキ, イッコウ and ナカタ, ダイスケ and ウチウミ, マサハル and ヒガシノ, カズユキ}
}