Taking the hypersonic axisymmetric inlet as the research object

firstly

parametric design of the inlet profile was carried out

and seven parameters

such as the general conic saturation

the general conic control line

the transition arc radius

the throat corner

the throat straight line to height ratio

the center line control parameter and the equivalent cone angle

were selected as the design variables to carry out the multi-objective design of the inlet. In the design process

the initial sample points were determined by orthogonal test design method

and Kriging surrogate models between two optimization objectives of inlet total pressure recovery coefficient and outlet distortion with design parameters were established. The surrogate model was analyzed and solved by the second generation of Non-Dominated Sorting Genetic Algorithm (NSGA-Ⅱ). The results showed that after multi-objective optimization

the total pressure recovery performance of the inlet increased by 263%

and the outlet distortion reduced by 2757%.