Based on the rotational method of characteristics and streamline tracing technique

the design method was developed for inward turning inlet with control of the axial and horizontal projections of intake

so as to meet the integrated design requirements of hypersonic vehicle waverider forebody and inlet with both sides intake layout. The inward turning inlet was designed utilizing this design method for the axial and horizontal projections of intake of super ellipse. Numerical simulation was conducted at design point Mach number of 6.0. The results indicate that the axial and horizontal projections of intake conform to the anticipated design. The inlet can retain the wave structure and pressure distribution of basic flowfield

and capture all of free incoming flow under the inviscid condition. Its performance of throat plane is almost equal to basic flowfield. Under the viscous condition

the inlet has high compression efficiency; the flow coefficient and total pressure recovery coefficient of exit plane are 0.96 and 0.56

respectively. This design method is feasible and effective.