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The paper presents the results of the ducted combustion test program on the supersonic mixing and combustion enhancement in scramjet combustor using aerated by gas (hydrogen or air) liquid kerosene (effervescent) jets injected through elliptic nozzles from tube-micropylons and fin-pylons. Kerosene jets were injected into two-dimensional diverging-area supersonic combustor in two ways: 1) through nozzles in tube-micropyl ons at an angle of 45 degrees relative to the mainstream air flow direction and 2) through the nozzles located at the base of fin-pylons. In the latter case co-flow injection was used. Tests were conducted at entrance Mach number M=2.5 and total temperature in the range Tt=1650-1800K. The tests results with using elliptic nozzles were compared to baseline results with circular nozzles. The axial static pressure distributions on the combustor walls and calculated pressure-area integrals showed that the effervescent kerosene sprays performed better for elliptic nozzles than for round nozzles at injection from tubemicropylons. Injection from fin-pylons did not show noticeable difference in combustion efficiency for elliptic and round nozzles.