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On the development of a jet noise prediction methodology.

机译：关于喷气噪声预测方法的发展。

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Computational Aeroacoustics (CAA), has emerged as a very important discipline and attracted significant attention lately. Strict sound emission regulations for aircraft and helicopters dictate the need to accurately predict the generation of sound emissions and their propagation in the far field. New computational tools are required employing high-order scheme with low dispersion and dissipation errors.; A study of a particular methodology, which relies on the use of highly accurate implicit compact finite difference schemes and implicit spatial filtering is presented in this work. A compact sixth-order method is employed. Spatial filtering is used as the means of rejecting unwanted numerical waves that emanate from the boundaries of the computational domain as a result of the discrete implementation of boundary conditions. State-of-the-art non-reflecting boundary conditions (i.e. Tam and Web's boundary conditions), that allow acoustic waves to freely exit the computational domain are used.; The above numerical methodology is the core of a new parallel Direct Numerical Simulation (DNS) code for compressible jet to be used for aeroacoustic purposes. This study presents an extensive validation of the core numerical methodology using two and three-dimensional jets and comparisons with analytical results with excellent agreement.
机译：计算航空声学（CAA）已成为一门非常重要的学科，最近引起了广泛的关注。飞机和直升机的严格声发射法规要求需要准确预测声发射的产生及其在远场中的传播。需要使用具有低色散和耗散误差的高阶方案的新计算工具。这项工作提出了一种对特定方法的研究，该方法依赖于使用高精度隐式紧致有限差分方案和隐式空间滤波。采用紧凑的六阶方法。空间滤波用作拒绝由于边界条件的离散实现而从计算域的边界发出的不需要的数值波的手段。使用允许声波自由离开计算域的最新非反射边界条件（即Tam和Web的边界条件）。以上数值方法是用于航空声学目的的可压缩射流新并行并行直接数值模拟（DNS）代码的核心。这项研究对使用二维和三维射流的核心数值方法进行了广泛的验证，并与分析结果进行了比较，具有很好的一致性。

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