The design method of the three-dimensional inward turning hypersonic jaws inlet was introduced. Corresponding design codes were developed. Thereafter

a CFD technology was used to verify this method and the design codes with the generated jaws inlet model under the height of 30km

design Mach number of 5 and attack angle of 0°

respectively. Finally

geometry and aerodynamic performances of jaws inlet under design conditions affected by the design parameters

such as the streamline tracing outlet profile

the compression angle set of base field and the design Mach number

were compared and analyzed. Result shows that compared with a low aspect ratio

the geometry performance will be better if the aspect ratio of rectangle-outlet approaches 2 with shorter total length and smaller surface area. Moreover

the compression angles should be set between 8° and 12° in preliminary design for relatively better performances

with the latter compression angle smaller than the former.