Abstract
The dynamics of reacting and non-reacting high temperature supersonic flowfields were investigated using advanced imaging and line-of-sight optical diagnostics. The measurements were made in a reacting flow shock tunnel facility generating Mach 3 air at static conditions of 1500 K and 0.3 atm. Hydrogen and helium were injected into the flow downstream of a rearward-facing step. Atomic oxygen in the free-stream air, produced in the reflected shock plenum, ensured prompt ignition at the H 2 -air interface. Planar Laser-Induced Fluorescence (PLIF) measurements of NO, also present in the free-stream air, determined the basic flow structure and temperature field for non-reactive flow with and without helium injection. PLIF measurements of OH revealed the instantaneous reaction zone interface for H 2 injection. The results provide insight into the turbulent mixing and burning phenomena in supersonic combusting flows.
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