The dual-mode operation was studied experimentally in a Mach 2.5 wind tunnel, to which a scramjet combustor model was connected directly. The total temperature and the total pressure of the air were 2000 K and 1.0 MPa, respectively. The air was heated in a vitiation heater. The mole fraction of oxygen was 21 %. Two kinds of the ramjet-mode operation and a scramjet-mode operation were attained. In a ramjetmode operation, the air was decelerated in the straight duct section. Subsonic combustion and the acceleration around the entrance of the divergent section followed. In another ramjet-mode, the air was decelerated in the divergent section, subsonic combustion followed, and the gas was choked at the exit of the combustor. These operating modes were attained in the same combustor and at the same fuel flow rate by changing the fuel injection position. There was no significant difference in the thrust increment among the three operating modes.
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