Asuccessive optimization strategy based on surrogate models was applied to integrated optimization of a hypersonic 2Dforebody/inlet.The sample data points were selected by Latin Hypercubes design of experiment technique

and the sample database was constructed by forebody/inlet flowfield numerical calculation using computational fluid dynamics(CFD) method based on2Dviscous Navier-Stokes equation.Four types of surrogate models including polynomial response surface

Kriging model

BPneural network and radial bases function neural network were adopted.As compared with baseline forebody/inlet at on-design state

the optimal forebody/inlet has better flow capture and compression and total pressure recover capability

and has lower drag force coefficient

with 5.3% improvement of overall performance.The performance of optimal forebody/inlet at off-design states has also improved to some extent.