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Restart Processes of Rectangular Hypersonic Inlets with Different Internal Contraction Ratios
AIAA Journal ( IF 2.5 ) Pub Date : 2021-03-01 , DOI: 10.2514/1.j059756
He-Xia Huang 1 , Hui-Jun Tan 1 , Jia Cai 1 , Shu Sun 1
Affiliation  

In this paper, the restart processes of two generic rectangular hypersonic inlets with different internal contraction ratios have been experimentally studied under a freestream Mach number of 5.0. The experimental results show that without downstream throttling, both inlets start successfully after the flowfield establishment of the wind tunnel. To obtain the restart processes of the two inlets, they are initially set at an unstarted state by a large downstream throttling ratio. Then, the throttling ratio is continuously decreased. For the inlet with a small internal contraction ratio, the restart process undergoes four stages: stable buzz, intermittent buzz, reestablishment of wave system in the inlet, and unthrottled flow; whereas for the inlet with a large contraction ratio, the internal flow cannot be normally reestablished after the intermittent buzz stage because a large-scale separation bubble consistently stands ahead of the inlet. That is, it cannot be restarted. In the stage of the intermittent buzz, there is a probability of the appearance of a quasi-steady flowfield when the pressure in the inlet reaches its maximum value, and the separation shock almost impinges on the cowl lip. For both inlets, the probability of buzz decreases continuously with time, and then it suddenly disappears. Furthermore, for the inlet with a large contraction ratio, two kinds of flowfields (that is, started or unstarted) occur at the same downstream throttling ratio and upstream flow conditions, which indicates that the inlet operates in the dual-solution region and the actual operating state of the inlet significantly depends on the historical flow. Therefore, the evaluation of hypersonic inlet starting capability must be examined carefully.



中文翻译:

具有不同内部收缩率的矩形高超声速进气口的重启过程

在本文中,在自由马赫数为5.0的情况下,对具有不同内部收缩率的两个通用矩形高超声速进气口的重启过程进行了实验研究。实验结果表明,在没有下游节流的情况下,两个入口均在风洞流场建立后成功启动。为了获得两个入口的重启过程,它们最初会通过较大的下游节流比设置为未启动状态。然后,节流比连续减小。对于内部收缩率小的入口,重新启动过程经历四个阶段:稳定的嗡嗡声,间歇性的嗡嗡声,入口中波系统的重新建立以及不节流。而对于收缩率大的进口,在间歇性的嗡嗡声阶段之后,内部流量通常无法恢复,因为大型分离气泡始终位于入口的前方。即,无法重新启动。在间歇性嗡嗡声阶段,当入口中的压力达到最大值时,可能会出现准稳态流场,并且分离冲击几乎会撞击到前围唇上。对于两个进气口,嗡嗡声的可能性会随着时间不断降低,然后突然消失。此外,对于具有较大收缩率的入口,在相同的下游节流比和上游流动条件下会出现两种流场(即已启动或未启动)。这表明进样口在双溶液区域中运行,并且进样口的实际运行状态在很大程度上取决于历史流量。因此,必须仔细检查高超音速进气口启动能力的评估。

更新日期:2021-03-02
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