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在总收缩比和内收缩比一定的前提下,对不同宽高比的侧板前掠高超声速进气道启动过程进行了研究,总结了宽高比对这类构型进气道启动性能的影响规律,对比了不同宽高比构型启动过程的差异,分析了造成这些差异的流动机理。结果表明:宽高比对侧板前掠二维进气道的启动马赫数有显著影响,宽高比3.0,4.5,6.0的进气道启动马赫数分别为3.5,3.9,4.6。不同宽高比不启动状态的共同特征,是内收缩段底板附近存在大规模流动分离,分离形成的溢流主要通过前掠侧板形成溢流窗口进行横向溢流,横向溢流对分离区流场结构有重要影响。在启动过程中,宽高比通过影响不启动状态分离区的展向尺度,影响了横向溢流对分离区排移效果,从而影响了进气道的启动性能。
Under the premise that the total shrinkage ratio and the internal shrinkage ratio are certain, the starting process of the frontal supersonic gas inlet with different aspect ratios is studied, and the effect of the aspect ratio on the performance of such inlet is also summarized The differences between the start-up processes of different aspect configurations were compared, and the flow mechanism that caused these differences was analyzed. The results show that the aspect ratio has a significant effect on the starting Mach number of the two-dimensional front air intake of the side plate, and the starting Mach number of intake passage with aspect ratios of 3.0, 4.5 and 6.0 are 3.5, 3.9 and 4.6, respectively. The common feature of different aspect ratios in non-activated state is the large-scale flow separation near the bottom of the internal shrinkage section. The overflow formed by the separation mainly transverses the overflow through the overflow window formed by the front-swept side plate, Field structure has an important influence. During start-up, the aspect ratio affects the scaling effect of the separation zone in the non-activated state, which affects the displacement effect of the lateral overflow on the separation zone, thus affecting the performance of the intake passage.