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Lambda shock behaviors of elliptic supersonic jets; a numerical analysis with modification of RANS turbulence model

机译：椭圆形超音速喷射器的λ震动行为; rans湍流模型改造的数值分析

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Supersonic jets have various applications in different industries, particularly as the propulsion of air-breathing engines and supersonic ejectors. The present study aimed to carry out a 3D numerical investigation of the outlet flow of elliptic nozzles of different aspect ratios and different length ratios of the convergent to the divergent part (called geometric ratio), as well as addressing the effect of tabs on the behavior of the outlet flow of the supersonic jet. In this regard, OpenFoam software was used alongside the pimple algorithm. First, the coefficients of the k-omega SST turbulence model were modified using experimental data, followed by the validation of the proposed method. The obtained results showed that beta* of 0.075 led to the best state of predicting the behavior of the jet outlet flow. Then, the modified turbulence model was applied to investigate the effect of aspect ratios (the ratio of the major to the minor length of the supersonic jet outlet) of 2.5, 3, and 4, geometric ratios of 1.672, 1.106, 0.738, 0.48, and 0.2878, and triangular, square, and semi-circular tabs on the behavior of the outlet flow of the supersonic jet. By changing the above ratios, regarding the change in the slope of the divergent part, the flow separation region was affected, and the boundary layer-shock wave interaction altered. Further, the results indicated a change in the structure of shock waves and, in turn, dissipation of the output energy was inevitable. (C) 2021 Elsevier Masson SAS. All rights reserved.
机译：超音速喷射器在不同行业中具有各种应用，特别是作为空气呼吸发动机的推进和超音速喷射器。本研究旨在对不同纵横比的椭圆形喷嘴的出口流和趋势与发散部分（称为几何比例）的不同长度比进行3D数值研究，以及解决Tabs对行为的影响超音速喷射的出口流动。在这方面，OpenFoam软件与疙瘩算法一起使用。首先，使用实验数据修改K-Omega SST湍流模型的系数，然后进行所提出的方法的验证。所得结果表明，0.075的β*导致了预测喷射出口流动的最佳状态。然后，应用修饰的湍流模型研究纵横比的效果（超音速喷射出口的主要长度的比例）为2.5,3和4，几何比为1.672,1.106,0.738,0.48，和0.2878和三角形，方形和半圆形突片上超声波射流出口流动的行为。通过改变上述比率，关于发散部分的斜率的变化，流动分离区域受到影响，并且边界层 - 冲击波相互作用改变。此外，结果表明了冲击波结构的变化，而且反过来，输出能量的耗散是不可避免的。 （c）2021 Elsevier Masson SAS。版权所有。

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