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为了发展适应宽飞行范围的高超声速二元进气道设计技术,考察了内收缩比对进气道特性的影响规律,并提出了结合附面层抽吸辅助自起动的大内收缩比进气道波系设计方法,改善了二元进气道低马赫条件下流量捕获低的弱点。研究发现,存在着设计点推力最优进气道内收缩比,而进气道非设计点流量系数随内收缩比而增大。基于最优内收缩比进气道构型,取消外压激波封口约束,通过局部等熵压缩波分散打进内收缩段内部,大幅提高了进气道低马赫流量捕获。并进一步通过合理配置内收缩段抽吸槽,以设计点(马赫6)1%,非设计点(马赫4)3%的流量损失使进气道自起动马赫数降到3.35,改善了内收缩比过大导致的自起动问题。
In order to develop a hypersonic binary inlet design that accommodates a wide range of flight, the influence of internal shrinkage ratio on inlet characteristics was investigated. A large internal contraction ratio intake combined with suction-assisted self-priming was proposed. The wave-line design approach improves the low-flow-capture weakness of the binary inlet under low Mach conditions. The study found that there is a design point thrust optimal in-port contraction ratio, and inlet non-design point flow coefficient increases with the internal contraction ratio. Based on the optimum inner-contraction ratio inlet configuration, the pressure-wave sealing constraint is canceled and the partial isentropic compression wave disperses into the inner contraction section, which greatly improves the low-Mach-flow inlet capture. Further, by reasonably arranging the suction section of the internal contraction section, the self-starting Mach number of the intake port is reduced to 3.35 at a flow rate of 1% of the designed point (Mach 6) and 3% of the non-designed point (Mach 4), thereby improving the internal contraction The problem of self-starting caused by too much.