Impact of mixture mass flux on hydrodynamic blockage ratio and Mach number of rotating detonation combustor

Tomoyuki Noda, Ken Matsuoka, Keisuke Goto, Akira Kawasaki, Hiroaki Watanabe, Noboru Itouyama, Jiro Kasahara, Akiko Matsuo

Research output: Contribution to journalArticlepeer-review


To analyze non-ideal phenomena, such as burned gas backflow and non-detonation combustion, which affect the rotating detonation wave Mach number, simultaneous self-luminous visualization, time-averaged static pressure, fluctuating pressure, and thrust measurements with gaseous ethylene and oxygen were performed. Consequently, by doubling the number density of the fuel injectors, the hydrodynamic blockage ratio at the oxidizer inlet increased approximately 1.7-fold under the same oxidizer inlet area conditions. This may be attributed to the increase in the detonation propagation Mach number owing to the enhanced mixing of fuel and oxidizer. The relationship between the parasitic combustion fraction in front of the rotating detonation wave and the Mach number was also investigated by using a distributed heat release model. Consequently, it was suggested that experimental Mach number decreased from approximately 4.1 to 2.8 with increase in a mixture mass flux, and the theoretical detonation wave propagation Mach number was 7.3.

Original languageEnglish
Pages (from-to)219-226
Number of pages8
JournalActa Astronautica
Publication statusPublished - 2023 Jun


  • Burned gas backflow
  • Detonation mach number
  • Non-detonation combustion
  • Pressure gain combustion
  • Rotating detonation combustor

ASJC Scopus subject areas

  • Aerospace Engineering


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