This paper presents the results of the numerical investigation of a hypersonic air flow in two different types of intake configurations of a scramjet engine. These configurations, referred as the internal compression intake system and the mixed compression intake system, are designed to operate at an altitude of 30 km and with an inlet air flow corresponding to a Mach number of 6.8. In order to investigate the general behavior of the flow, a set of RANS simulations were performed for both cases. The results show relevant details of the flow such as the proper capturing of the shock wave fronts, the engine compression performance and the spatial development of the flow through the engine. In general, a substantial amount of similarities concerning the flow behavior are observed when both configurations are directly compared. A quantitative analysis centered in specific parameters describing the compression of the inlet flow, e.g., the adiabatic compression efficiency, indicates minor differences when these parameters are assessed. Nevertheless, additional considerations reveal a greater versatility of the internal intake system; for instance, an analysis of the spatial development of the boundary layer flow, as quantified by the velocity profiles of the flow extracted at different locations, suggests better mixing properties in comparison with the mixed intake system. The latter effect is desirable since mixing enhancement in the combustion chamber can help to achieve stable conditions for supersonic combustion.

本文介绍了两种不同类型的超燃冲压发动机进气配置中高超音速气流的数值研究结果。这些配置被称为内部压缩进气系统和混合压缩进气系统，设计用于在 30 公里的高度和对应于 6.8 马赫数的进气流量。为了研究流的一般行为，一组RANS对这两种情况都进行了模拟。结果显示了流动的相关细节，例如正确捕获冲击波前、发动机压缩性能和通过发动机的流动的空间发展。一般来说，当直接比较两种配置时，会观察到大量关于流动行为的相似之处。以描述入口流压缩的特定参数（例如绝热压缩效率）为中心的定量分析表明，评估这些参数时存在细微差别。然而，额外的考虑表明内部进气系统具有更大的多功能性；例如，边界层流的空间发展分析，通过在不同位置提取的流的速度剖面进行量化，表明与混合进气系统相比具有更好的混合性能。后一种效果是理想的，因为燃烧室中的混合增强可以帮助实现超音速燃烧的稳定条件。