New regulations are imposing noise emissions limitations for the aviation industry which are pushing researchers and engineers to invest efforts in studying the aeroacoustics phenomena. Following this trend, an in-house computational fluid dynamics tool is build to reproduce high fidelity results of supersonic jet flows for aeroacoustic analogy applications. The solver is written using the large eddy simulation formulation that is discretized using a finite difference approach and an explicit time integration. Numerical simulations of supersonic jet flows are very expensive and demand efficient high-performance computing. Therefore, non-blocking message passage interface protocols and parallel Input/Output features are implemented into the code in order to perform simulations which demand up to one billion grid points. The present work addresses the evaluation of code improvements along with the computational performance of the solver running on a computer with maximum theoretical peak of 2.727 PFlops. Different mesh configurations, whose size varies from a few hundred thousand to approximately one billion grid points, are evaluated in the present paper. Calculations are performed using different workloads in order to assess the strong and weak scalability of the parallel computational tool. Moreover, validation results of a realistic flow condition are also presented in the current work.

中文翻译：

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用于超音速射流配置的 CFD 工具的可扩展性

新法规对航空业施加了噪声排放限制，这促使研究人员和工程师投入精力研究气动声学现象。遵循这一趋势，构建了一个内部计算流体动力学工具，以重现用于气动声学类比应用的超音速射流的高保真结果。求解器是使用大涡模拟公式编写的，该公式使用有限差分方法和显式时间积分进行离散化。超音速射流的数值模拟非常昂贵，需要高效的高性能计算。因此，在代码中实现了非阻塞消息传递接口协议和并行输入/输出功能，以执行需要多达 10 亿个网格点的模拟。目前的工作涉及代码改进的评估以及在计算机上运行的求解器的计算性能，最大理论峰值为 2.727 PFlops。本文评估了不同的网格配置，其大小从几十万到大约十亿个网格点不等。使用不同的工作负载执行计算，以评估并行计算工具的强弱可扩展性。此外，当前工作中还提供了现实流动条件的验证结果。在本文中进行了评估。使用不同的工作负载执行计算，以评估并行计算工具的强弱可扩展性。此外，当前工作中还提供了现实流动条件的验证结果。在本文中进行了评估。使用不同的工作负载执行计算，以评估并行计算工具的强弱可扩展性。此外，当前工作中还提供了现实流动条件的验证结果。