2026-03-05T08:52:34Z https://nagoya.repo.nii.ac.jp/oai

oai:nagoya.repo.nii.ac.jp:02003924 2023-01-16T04:59:15Z 673:674:675

Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel Nakata, Kotaro Ota, Kosei Ito, Shiro Ishihara, Kazuki Goto, Keisuke Itouyama, Noboru Watanabe, Hiroaki Kawasaki, Akira Matsuoka, Ken Kasahara, Jiro Matsuo, Akiko Funaki, Ikkoh Higashino, Kazuyuki Braun, James Meyer, Terrence Paniagua, Guillermo Converging–diverging nozzles are common in rocket engine systems to increase the exhaust velocity and improve thrust performance. In this study, we focused on the acceleration of subsonic burned gas without a structural throat via detonation to realize a simple and compact engine. We developed and tested a rotating detonation engine (RDE) without a throat and with a diverging channel (constant diverging angle α=5  deg). Gaseous C2H4 and O2 were used as the propellants, and the mass flow rate ranged from 62 to 134  g/s in the combustion tests under low back-pressure conditions. We measured pressure and thrust, as well as high-speed imaging of self-luminescence of the combustion and imaging of the exhaust plume. The pressure at the exit was less than one-fifth of the maximum pressure in the RDE, significantly below the value for a sonic flow. The results suggested that the exhaust flow was supersonic, with values up to Mach 1.7, without the need of a converging section within the engine. In addition to the estimated Mach number from the measured pressure, the exhaust plume images coherently indicated the existence of supersonic exhaust. journal article American Institute of Aeronautics and Astronautics 2022-07 application/pdf AIAA Journal 7 60 4015 4023 0001-1452 https://nagoya.repo.nii.ac.jp/record/2003924/files/AIAAJournal_revision_without_correction_footnote_forRepository.pdf http://hdl.handle.net/2237/0002003924 https://nagoya.repo.nii.ac.jp/records/2003924 eng https://doi.org/10.2514/1.J061300