Advance in supersonic combustion modelling and simulations

A. Ingenito, C. Bruno, E. Giacomazzi, J. Steelant

Research output: Contribution to conferencePaper

4 Citations (Scopus)

Abstract

Mixing and combustion of supersonic reacting flows are currently under investigation for scramjet engines. Experimental results at NASA-Langley RC with single-jet hydrogen injection at Mach 2.5 in a Mach 2 airstreams showed combustion taking place in a very short lenght: this indicates that supersonic combustion may indeed be very fast. Numerical simulations of the same test case have also done using LES and the subgrid scale model, ISCM, developed purposely for supersonic combustion. This model accounts for the effects of compressibility on reaction rate and on mixing. Numerical simulations indicate that the flame is unsteady: it anchors at about 15 cm from the injector, develops downstream and lifts off. Periodical ignition and quenching have been investigated by means of frequency analysis.
Original languageEnglish
Publication statusPublished - 2007
Event45th AIAA Aerospace Sciences Meeting 2007 - , United States
Duration: 1 Jan 2007 → …

Conference

Conference45th AIAA Aerospace Sciences Meeting 2007
CountryUnited States
Period1/1/07 → …

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All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Ingenito, A., Bruno, C., Giacomazzi, E., & Steelant, J. (2007). Advance in supersonic combustion modelling and simulations. Paper presented at 45th AIAA Aerospace Sciences Meeting 2007, United States.