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设计并研究了一种基于双模态燃烧的二元高超声速进气道.通过在进气道内设计一个隔板,将流道分为超声速通道和亚燃通道.采用数值模拟方法,研究了内压段肩部型面,隔板进口高度及水平位置,过渡段起始点及扩张角、下通道出口高度、隔板头部型面等几何设计参数对进气道性能的影响规律,并给出了参数选择建议.结果表明:在研究范围内,内压段肩部型面、隔板进口高度及水平位置和过渡段起始点对总压恢复系数影响较大;而隔板进口高度及头部型面、过渡段扩张角和下通道出口高度对抗反压能力有较大影响.
A bimodal hypersonic air inlet based on dual-mode combustion is designed and researched. The flow channel is divided into supersonic channel and sub-combustion channel by designing a partition in the air inlet channel. The influence of geometric design parameters such as shoulder profile of partition, inlet height and horizontal position of bulkhead, initial point of transitional section and expansion angle, exit height of lower channel, head profile of partition on inlet performance are given. The results show that: within the scope of the study, the height of the shoulder section of the internal pressure section, the inlet height of the bulkhead and the starting point of the transition section have a great influence on the total pressure recovery coefficient; while the inlet height of the bulkhead and the head Profile, the transition section of the expansion angle and the outlet height of the lower channel against backpressure have a greater impact.