Experimental Study on Truncated Conical Rotating Detonation Engines with Diverging Flows

Kotaro Nakata, Kosei Ota, Shiro Ito, Kazuki Ishihara, Keisuke Goto, Itouyama Noboru, Hiroaki Watanabe, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution


This study focused on acceleration of propellant to supersonic speed with a compact engine. Increase in the exhaust velocity of a rocket engine leads to improvement of the thrust performance. Several combustion tests were conducted for a small rotating detonation engine (RDE) whose channel is truncated conical shaped (diverging angle (formula presented)), under low back pressure conditions. In these tests, gaseous (formula presented) were used as the propellant, and the mass flow rate were ranged from 56 to 123 g/s. The pressure ratio between the maximum value in the engine and at the exit was approximately 0.16, which was confirmed to be significantly below the critical value for a sonic flow. Namely, the exhaust flow was supersonic, even though there was no convent section in the engine. In a range of propellant mass flow rate, specific impulses were approximately 110% compared to those in a cylindrical RDE with a uniform cross-section combustor.

ホスト出版物のタイトルAIAA Propulsion and Energy Forum, 2021
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
出版ステータスPublished - 2021
イベントAIAA Propulsion and Energy Forum, 2021 - Virtual, Online
継続期間: 2021 8月 92021 8月 11


名前AIAA Propulsion and Energy Forum, 2021


ConferenceAIAA Propulsion and Energy Forum, 2021
CityVirtual, Online

ASJC Scopus subject areas

  • エネルギー(全般)
  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学
  • 機械工学


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