A feasible design principle was developed by combining a series of design and performance predicting methods of typical two-dimensional hypersonic inlets.The design methods of inlet entrance

external compression shocks

internal contraction tunnel

cowl and isolator were presented at the given flux

pressure rise ratio and working range(starting Mach number and capability of enduring back pressure).A preliminary design of hypersonic inlet at the design point of H=22 800 m

Ma0=6 was conducted

so the performance parameters(pressure rise ratio

Mach number

temperature rise ratio and total pressure recovery)

starting Mach number and capability of enduring back pressure were predicted and calculated with small error.With this method

the inlet could present simple construction

high flow coefficient and low compression loss in developing a satisfactory model without optimization.