With constraint of all performance indexes

the integrated design of forebody/inlet and the wind tunnel test of hypersonic vehicle was developed

while the major performance of forebody/inlet was assessed. Results showed that:(1)the performances of forebody/inlet satisfied all the performance indexes at the design condition

and the wind tunnel test validated the numerical design method; (2)the numerical results agreed well with the wind tunnel test results

the max error of mass flow ratio was 4% and the max error of total pressure recovery coefficient was 42%

so the numerical method was efficient;(3)the additional drag of forebody/inlet increased with the increasing of inflow Mach number

the additional drag was up to 172% of the total drag at the angle of attack 0° when the Mach number was 4

which should be considered in the design;(4)the prearranged planning should be made to avoid failure of the wind tunnel test because the inlet may not be able to start

which should be considered during design of the wind tunnel test scheme.