Experiments on the structure of an annular compressible reacting shear layer

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 H 2 -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