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⁺

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⁺