Abstract
An experimental investigation was performed to characterize liquid fuel injection into a Mach 2.1 air ow simulating a scramjet combustor ow eld. In particular, ethanol fuel penetration and dispersion characteristics were compared for a transverse injection con guration with and without a mixing enhancement n. In previous studies involving gaseous fuel, the n-guided injection not only improved turbulent mixing but also served to reduce the stagnation pressure loss associated with the fuel injection shock. To characterize the mixing between liquid fuel and air, laser-sheet visualization of the cross-sectional view and schlieren visualization of the side view were obtained at various time intervals. Wall pressure measurements along the axial direction were used to help interpret the visualization data. The side views of fuel injection revealed that the fuel penetration height in the neareld was twoto six-times greater with the n-guided injection. Also, downstream evolution of the liquid-fuel cross-sectional area suggested a greater vaporization rate associated with the n-guided injection. The present results showed a signi cant improvement in key injection parameters and mixing characteristics associated with n-guided liquid-fuel injection.
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