Effects of multiple subcavities with floor subcavity in supersonic cavity flow

IF 5.4 2区工程技术 Q1 ENGINEERING, AEROSPACE

Propulsion and Power Research Pub Date : 2023-03-01 DOI:10.1016/j.jppr.2023.02.003

Priyansh Jain, Anbarasan Sekar, Aravind Vaidyanathan

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Abstract

Experimental and computational analysis has been carried out by many researchers on supersonic cavity flow, but detailed analysis based on Rossiter's model still requires some insight. In the current study an open rectangular cavity with a length to depth ratio of 2 (L/D = 2) and Mach number at the inlet as 1.71, was considered as a baseline configuration for experimental analysis. Statistical techniques such as power spectral density (PSD), correlation, and overall sound pressure level (OASPL) were carried out on the unsteady pressure data, to analyze the aero-acoustic flow physics. High-speed schlieren images were processed to obtain spatially coherent modes by proper orthogonal decomposition (POD). The analysis was extended for different dimensions of subcavities on the aft, floor, and front wall. This detailed analysis of these configurations with different dimensions and combinations revealed the various flow features and mode frequencies in supersonic cavity. As the front wall subcavity act as a passive control device, reducing the overall sound pressure level inside the cavity whereas, the aft wall subcavity acts as a passive resonator with distinct harmonic fluid-resonant modes, a similar phenomenon was observed for floor subcavity at different locations. A novel method was employed to analyze Rossiter's model and its applicability in estimating experimental modes was verified, as it accurately predicted the dominant frequencies with a maximum of 2.74% uncertainty among all the configurations.

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超音速空腔流动中多个亚空腔与底亚空腔的影响

许多研究者已经对超声速空腔流动进行了实验和计算分析，但是基于Rossiter模型的详细分析还需要一些深入的了解。在本研究中，将长深比为2 (L/D = 2)、进口马赫数为1.71的开放矩形空腔作为实验分析的基准配置。采用功率谱密度(PSD)、相关系数(correlation)、总声压级(OASPL)等统计方法对非定常压力数据进行分析。采用正交分解(POD)方法对高速纹影图像进行处理，得到空间相干模式。将分析扩展到不同尺寸的尾部、底板和前壁上的亚腔。通过对这些不同尺寸和组合的构型的详细分析，揭示了超声速腔内不同的流动特征和模态频率。由于前壁亚腔作为被动控制装置，降低了腔内的整体声压级，而后壁亚腔作为被动谐振器，具有不同的谐波流-谐振模式，因此不同位置的底板亚腔也有类似的现象。采用一种新颖的方法对Rossiter模型进行分析，验证了Rossiter模型在实验模态估计中的适用性，该模型准确地预测了所有构型的主导频率，最大不确定度为2.74%。

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来源期刊

Propulsion and Power Research Multiple-

CiteScore

7.50

自引率

5.70%

发文量

期刊介绍： Propulsion and Power Research is a peer reviewed scientific journal in English established in 2012. The Journals publishes high quality original research articles and general reviews in fundamental research aspects of aeronautics/astronautics propulsion and power engineering, including, but not limited to, system, fluid mechanics, heat transfer, combustion, vibration and acoustics, solid mechanics and dynamics, control and so on. The journal serves as a platform for academic exchange by experts, scholars and researchers in these fields.