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Combustion efficiency was measured for a supersonic, non-premixed, jet-like flame. The flame was stabilized along the axis of a Mach 2.5 wind tunnel and wedges were mounted on the sidewalls in order to produce oblique shocks that interacted with the flame. Data was taken with air at stagnation temperatures of 284 K and 497 K, at various fuel flow rates. Efficiency was measured using a solid state hydrogen gas detector that analyzed exit flue gas. It was observed that moving the wedges to different down-stream locations affected the visible flame length, but had only minor impact on the combustion efficiency in both air temperature case. The oblique shocks produced about a 8% reduction in combustion efficiency at 284 K, with wedge position changing the fuel flow level needed to see certain characteristics. The reduction in efficiency and matching reduction in flame length are due to the shock waves. The shock waves cause radial inflow and outflow that allows some of the fuel to escape unburned. In the 497 K case, this same flow pattern causes a decrease when the flame is small and is not large enough to heat a significant portion of the air around it; but, this same flow pattern boosts combustion efficiency when the core of the flame is sufficiently large.

Effects of shock waves on combustion efficiency of supersonic flames