Experimental investigation of terminal shock sensors for mixed-compression inlets
Experimental investigation of terminal shock sensors for mixed-compression inlets
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DOI：
10.2514/3.23457
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发表时间：
1992-02
影响因子：
1.9
通讯作者：
M. Sajben;J. Donovan;M. Morris
中科院分区：
文献类型：
--
作者：
M. Sajben;J. Donovan;M. Morris
本文描述了在高超音速飞行条件下，为非侵入式检测混合压缩进气道末级激波位置而设计的装置的实验研究。选择了基于壁装传感器阵列的壁面压力传感系统进行详细研究。压力信号通过三种不同的方法处理：(1)解释瞬时压力分布，(2)检测激波时发生的湍流强度放大，(3)确定在通道下游引入的搜索音可以传播到的上游极限。这些方法中的前两种是实时测试的。第三种方法似乎只适用于弱激波；在高激波强度时，无法检测到震源上游的传播。
This paper describes experimental investigations of devices designed for the nonintrusive detection of terminal shock location in mixed-compression inlets at high supersonic flight speeds. Systems based on sensing wall pressures by an array of wall-mounted transducers were selected for detailed study. Pressure signals were processed by three different methods: (1) interpretation of instantaneous pressure distributions, (2) detection of the turbulent intensity amplification occurring at the shock, and (3) determination of the upstream limit to which a search-tone, introduced at the downstream end of the channel, can propagate. The first two of these methods were tested in real time. The third method appeared feasible for weak shocks only; at high shock strengths, propagation upstream of the source could not be detected.