Abstract: A new internal waverider inlet which has regular rectangular shape of intake and exit is designed at Ma=6.0. It is based on the basic flowfield which has even performance at exit plane and derived with the technology of stream tracing and shock-cutting. Comparisons are made between the newly designed inlet and a typical sidewall compression inlet. The design Mach number and incoming shape of this new inlet are chosen according to the sidewall compression inlet. Numerical results show that most of the performance parameters of the internal waverider inlet are a bit higher than the sidewall inlet, such as the mass capture ratio, total pressure recovery and the kinetic efficiency. Two inlets at off-design points are compared as well. The internal waverider inlet can capture more than 91% of the incoming flow at off-design points simulated and 98% of the incoming flow at design point. The results prove that Internal Waverider Inlet using special technologies which lead to three dimensional compression as well as high mass capture ratio is a kind of fixed-geometry inlet with good performance.

Key words: Hypersonic inlet； Internal waverider inlet； Sidewall compression inlet； Flow capture⁺； Total pressure recovery⁺

摘要： 采用流线追踪技术,基于一种有利于均匀性的基本流场,按内乘波式进气道设计方法生成了一个来流马赫数6.0且进出口形状均为矩形的内乘波式进气道。其设计马赫数、迎风面形状等因素均参照某典型侧压式进气道选取,以便与之对比。CFD计算结果给出了设计状态下该内乘波式进气道与某典型侧压式进气道的流量系数、总压恢复、动能效率等主要性能指标,发现该内乘波式进气道的各项性能参数均略优于侧压式进气道。在非设计马赫数、攻角、侧滑等非设计状态下类似的性能对比研究表明,该内乘波式进气道不仅在设计状态下可捕获98%的来流,而且在各非设计状态下也可捕获91%以上的来流,流量捕获性能优势明显。以上结果证实:实现三维压缩与激波贴口的内乘波式进气道是一种高性能的定几何进气道方案。

关键词: 高超声速进气道;内乘波式进气道;侧压式进气道;流量捕获⁺;总压恢复⁺