Abstract: To assign the compression ratio on the surface of inner cone reasonably and improve the compression efficiency of inlet remarkably，an innovative Mach number decelerated law with minor changes on the middle section of the inner cone surface was examined. The results indicate that the compression loss under unit pressure ratio of innovative Mach number decelerated law，compared with that of arc tangent Mach number distribution，reduces by 20%. In order to improve the performance of basic flow field，an inverse design method of center body based on the controlled flow angle distribution was proposed，and thus the base flow field can be inversely designed by the double controlled distributions of Mach number on the inner cone wall and flow angle on the center body surface. In addition，the impact of basic flow field on the hypersonic inward turning inlet was also investigated. The results demonstrate that the compression loss can be reduced markedly by inversely designing the shape of center body under destined flow angle distributions. To be specific，compared with the constant center body，there is at least 34% decrease on the compression loss so that the performance of the inward turning inlet can be enhanced.

Key words: Hypersonic inward turning inlet；Mach number decelerated law；Axisymmetric basic flow field；Inverse design；Flow angle distribution

摘要： 为了合理控制内锥面压缩强度的份额、提高进气道压缩效率，提出了一种内锥面中间段压缩较缓的新型马赫数减速规律，结果表明新型马赫数减速规律的单位压比压缩损失相对于反正切马赫数分布降低了20%。为了进一步改善基准流场，提出了基于流动角分布可控的中心体反设计方法，实现了内锥面马赫数分布和中心体表面流动角分布双重可控的基准流场反设计。此外，还研究了该基准流场对内转进气道性能的影响。结果表明，通过中心体表面流动角分布反设计中心体构型可显著降低基准流场压缩损失，相比于等直中心体损失至少降低了34%，从而提高了内转进气道性能。

关键词: 高超内转进气道；马赫数减速规律；轴对称基准流场；反设计；流动角分布