MEASUREMENTS OF OH AND H2O FOR REACTING FLOW IN A SUPERSONIC COMBUSTING RAMJET COMBUSTOR

Mixing and combusting high-enthalpy flows, similar to those encountere d in supersonic combusting ramjet engines, were investigated using a s hock tunnel to produce the now in conjunction with nonintrusive optica l diagnostics that monitored the performance of two injector configura tions, The shock tunnel was configured to produce Mach 3 flow and stag nation enthalpies corresponding to flight equivalent Mach numbers betw een 7-11. A pulsed hydrogen injection capability and interchangeable i njector blocks provided a means of examining high-speed, high-enthalpy reacting flows, Planar laser induced fluorescence of ON radicals in t he near-injector region produced images that show the combusting and m ixing zones fur the reacting flow, Line-of-sight exit plane measuremen ts of water concentration and temperature were used to provide a uniqu e method of monitoring exit plane products, Near-injector mixing dynam ics and exit plane compositions were compared for wall jet and axial i njection systems. In addition, exit plane measurements indicated that a quasi-steady-state condition was achieved during the 1- to 2-ms test times.