Design and study of a two-dimensional hypersonic inlet based on dual-mode combustion was conducted.The duct was divided into a supersonic duct and a subsonic combustion duct by a splitter plate.The influence of the geometry parameters on the inlet performance was mainly studied by using numerical method.The geometry parameters included the profile of the shoulder

the height and position of splitter plate

the turning position and expansion angle of transition duct

the height of subsonic combustion duct and the shape of the head of splitter plate.Results indicate that the profile of the shoulder

the height and position of splitter plate

the turning position of transition duct have great effects on the total pressure recovery coefficient

while the height of splitter plate

the shape of the head of splitter plate

the expansion angle of transition duct and the height of subsonic combustion duct have great effects on characteristics of back pressure.