Several direct-connect hot tests were done for a variable-area propelling nozzle dual-mode ramjet model combustor on the simulated fly condition of Ma=6 and H=25km. By use of the variable-area propelling nozzle

ignition performance and thrust of the dual-mode combustor were improved. Once flame can be hold in the combustor during subsonic combustion procedure

the supersonic combustion can be achieved by adjusting nozzle area thus a mode transition can be realized also. Finally

It is promising that the operating region of a fixed-geometry dual-mode ramjet can be extended by the variable-area propelling nozzle which simplified a fully variable dual-mode ramjet.