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.

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大量精力研究航空声学现象。遵循这一趋势，建立了内部计算流体动力学工具，以再现超音速射流的高保真度结果，用于航空声学类比应用。求解器使用大型涡流仿真公式编写，该公式使用有限差分法和显式时间积分离散化。超声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，以便执行需要多达十亿个网格点的仿真。本工作解决了代码改进的评估以及在最大理论峰值为2.727 PFlops的计算机上运行的求解器的计算性能。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。为了评估并行计算工具的强和弱可伸缩性，使用不同的工作负载执行了计算。此外，当前工作中还给出了实际流动条件的验证结果。在本文中进行了评估。为了评估并行计算工具的强和弱可伸缩性，使用不同的工作负载执行了计算。此外，当前工作中还给出了实际流动条件的验证结果。在本文中进行了评估。为了评估并行计算工具的强和弱可伸缩性，使用不同的工作负载执行了计算。此外，当前工作中还给出了实际流动条件的验证结果。