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针对二元高超声速进气道宽马赫数大攻角工作要求,研究了转动唇口变几何进气道调节方案,给出了一种高性能变几何原型进气道设计方法,并通过数值仿真获得了变几何进气道各工况下的调节规律及性能变化规律。研究表明:采用特殊曲面唇口设计的变几何进气道宽马赫数范围内流场结构较好,总体性能优越;以马赫数Ma=6.0为设计点的原型进气道采用转动唇口方案无需附面层抽吸即可在唇口开启过程中实现接力点自起动,且最低自起动马赫数降至Ma=3.5;低马赫数大攻角状态下,通过转动唇口合理控制喉部平均马赫数范围可保证进气道正常工作。
Aiming at the work requirement of high Mach number wide angle attack of binary hypersonic air inlet, this paper studies the variable geometry inlet adjustment scheme of rotating lip, and presents a high performance variable geometry prototyping inlet design method. Through numerical simulation Obtained a variable geometric inlet conditions under various regulation and performance changes. The results show that the flow field structure is better and the overall performance is superior in the wide Mach number range of the variable geometry inlet with the special curved surface lip design. The prototype inlet with the Mach number of 6.0 is not required In the process of lip opening, the starting point of self-starting relay can be realized, and the minimum self-starting Mach number decreases to Ma = 3.5. Under the condition of high Mach angles, the throat average Mach Number of ranges to ensure that the inlet normal work.