The design method of axisymmetric wall boundary with a controllable law of wall pressure rise was investigated using the theory of rotational characteristics.With this design method

multi-objective optimization of the compression surface was carried out on the basis of surrogate models

and then a hypersonic axisymmetric inlet was designed using the optimal solutions.The inlet was investigated through numerical simulation

and was compared with the normal double-cone and triple-cone inlet.The results show that the length of new inlet is reduced by 32.5% of the radius than the double-cone inlet;under the design point

the performance of the new inlet lies between the double-cone and triple-cone inlet;under the start point

the flow capture ratio is improved by 8.24% and 12.60%

and the total pressure recovery is improved by 4.06% and 2.50% than the double-cone and triple-cone inlet

respectively.