Experiments on the structure of an annular compressible reacting shear layer

R. S. Barlow, D. C. Fourguette, M. G. Mungal, R. W. Dibble

Research output: Contribution to journalArticlepeer-review

16 Scopus citations


An axisymmetric burner for the study of compressible reacting shear layers is described, and the ranges of its operating parameters are analyzed. This burner has a central supersonic freejet of resistively heated air, surrounded by a low-speed co-flow of fuel-rich Hi-air combustion products. Planar laser-induced fluorescence imaging of OH is used to visualize the structure of the annular reacting shear layer in the near field of the jet. Images from two cases with convective Mach numbers of 0.11 and 0.41 are presented and discussed in terms of previously reported results for nonreacting compressible shear layers. Observed effects of compressibility on the structure and growth rate of the reacting annular shear layer are similar to effects reported in nonreacting flows. Results from a compressible “lifted” flame and from the reaction zone at the boundary of an underexpanded jet are presented.

Original languageEnglish (US)
Pages (from-to)2244-2251
Number of pages8
JournalAIAA journal
Issue number9
StatePublished - Sep 1992
Externally publishedYes

ASJC Scopus subject areas

  • Aerospace Engineering


Dive into the research topics of 'Experiments on the structure of an annular compressible reacting shear layer'. Together they form a unique fingerprint.

Cite this