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为深入了解大规模分离区在进气道启动过程中的变化规律、影响因素及自持机理,针对简化的二维高超声速进气道加速启动过程进行了数值研究,对比了不同唇口角构型的启动性能、启动过程和分离区变化规律,分析了其中的流动机理。结果表明:(1)上壁面单侧压缩的二维进气道启动性能受唇口角影响显著,随着唇口角从0°增加到12°,启动马赫数呈现先减小后增加的趋势,4°时启动马赫数最小。(2)不同唇口角构型不启动状态都存在大规模分离区,分离区的前半部分接近一致,后半部分差异明显。(3)在加速启动过程中,分离区主要依靠分离激波在上壁面的反射激波维持自身的存在,不同的唇口角构型在相同来流马赫数下分离激波在上壁面的反射激波强度不同,这影响了分离区的自持能力,从而影响了启动性能。
In order to deeply understand the variation rules, influential factors and self-sustaining mechanism of large-scale separation zone in the intake passage start-up process, a numerical study on the simplified two-dimensional hypersonic inlet acceleration start process was carried out. Comparing the different lip angle configuration Start-up performance, start-up process and the separation of changes in the law, analysis of the flow mechanism. The results show that: (1) The starting behavior of the two-dimensional inlet with unilateral compression on the upper wall is significantly affected by the lip angle. As the lip angle increases from 0 ° to 12 °, the starting Mach number tends to decrease first and then increase. 4 ° minimum starting Mach number. (2) There is a large-scale separation zone in different lip-angle configuration without starting state. The first half of the separation zone is close to the same and the second half is obviously different. (3) During the accelerated start-up process, the separation zone mainly relies on the separation shock to maintain its own existence on the upper wall. The different lip-angle configurations separate the shock excitation on the upper wall at the same Mach number Wave intensity is different, which affects the self-sustaining ability of the separation zone, thus affecting the startup performance.