Performance evaluation of scramjet combustors using kinetic energy and combustion efficiencies

Goro Masuya, Tomokazu Uemoto, Yoshihiro Wakana, Kenji Kudou, Atsuo Murakami, Tomoyuki Komuro

Research output: Contribution to journalArticlepeer-review

11 Citations (Scopus)


A performance parameter of scramjet combustors was introduced on the basis of thrust. It was written in terms of the kinetic energy and combustion efficiencies. To evaluate this parameter from available data of direct connect combustor experiments, ideal nozzle calculation was carried out for each stream tube, starting from the data at the combustor exit, and the results were integrated across the nozzle exit to obtain the efficiencies and performance parameter. The relative importance of heat release and aerothermodynamic losses were compared for various configurations of the fuel injectors and combustor ducts. For flight Mach numbers less than 7, the heat release had a stronger influence on the performance than the losses. The optimum length, where the effects of both effects canceled each other, was 15-20 times the flow section width for the rectangular section combustor with perpendicular wall injectors.

Original languageEnglish
Pages (from-to)401-407
Number of pages7
JournalJournal of Propulsion and Power
Issue number3
Publication statusPublished - 1999 Jan 1

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science


Dive into the research topics of 'Performance evaluation of scramjet combustors using kinetic energy and combustion efficiencies'. Together they form a unique fingerprint.

Cite this