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An opposed flow burner is examined as an instrument to screen and characterize fuel before full-scale hybrid rocket testing. This device requires small amounts (∼10 g) of solid fuels, and it can save time and material in early phases of fuel characterization. Although impinging jet configurations have been investigated in the past, the full range of operation of these systems in terms of hybrid rocket motor flowfield conditions has not been fully explored. The regression rate, flame structure, and flame temperature in an opposed burner configuration is investigated, and an analysis to relate the results to hybrid rocket applications is developed. Hydroxyl-terminated polybutadiene, dicyclopentadiene, and paraffin are investigated via an opposed flow burner over an oxidizer mass flux range of 4 to 25 kg∕s∕m 2 . Results show solid-fuel regression rate sensitivity to laminar and turbulent flow regimes. Aluminized hydroxyl-terminated polybutadiene regresses ∼34% slower than neat fuel in the opposed flow burner. Infrared spectroscopy reveals peak flame temperatures of the samples tested, ranging from 1850 to 2100 K. Although the opposed flow burner is not a perfect representation of hybrid rocket motor operation, it may prove useful in smallscale screening of fuels.

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