中文摘要：

采用有旋特征线理论,研究了沿程压升规律可控的轴对称物理壁面设计方法,基于该方法,结合替代模型多目标优化设计压缩面,基于优化结果,设计了一种高超声速轴对称进气道,对其进行了数值研究,并与常规双锥、三锥轴对称进气道进行了比较.结果表明：该进气道长度比双锥进气道缩短捕获半径的32.5%;设计点其性能介于双锥与三锥之间;起动点其流量系数比双锥和三锥分别提高8.24%和12.60%,总压恢复系数比双锥和三锥分别提高4.06%和2.50%.

英文摘要：

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.