Hybrid RANS/LES of a supersonic combustor

David M. Peterson, Graham V Candler

Research output: Contribution to journalConference articlepeer-review

12 Scopus citations


Preliminary results from simulations modeling flush wall fuel injection in scramjet engines is presented. The simulations use a hybrid Reynolds-averaged Navier-Stokes and large eddy simulation methodology, where the primary function of the RANS mode is to act as a wall model for the large eddy simulation. The hybrid method is based on the delayed detached-eddy simulation formulation and includes improvements for functioning as a wall-modeled large eddy simulation. A seven species, eight reaction mechanism for hydrogen-air chemistry is coupled with the flow solver. The results presented here do not include the effects of subgrid turbulence-chemistry interaction. The instantaneous structure and ignition characteristics of a transverse jet of hydrogen in a supersonic crossflow is compared to planar laser induced fluorescence of OH radicals. The chemical mechanism used results in aut oignit ion of the jet. The thin, wrinkled filament of OH observed in the experiment is reproduced well by the simulation. A model hydrogen-powered scramjet combustor for which there are internal measurements of temperature and species concentration, as well as wall pressure measurements, was also simulated. Well into the simulation a combustion front develops within the combustor that propagates upstream. As of the time this paper was written, the front is still moving upstream. The development of the combustion front it discussed and initial comparisons to the experimental data are made. The initial comparisons are promising, showing mean flow quantities that are qualitatively similar to what is measured experimentally.

Original languageEnglish (US)
JournalCollection of Technical Papers - AIAA Applied Aerodynamics Conference
StatePublished - Sep 17 2008
Event26th AIAA Applied Aerodynamics Conference - Honolulu, HI, United States
Duration: Aug 18 2008Aug 21 2008


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