关于超音速喷流外形的CFD工具的scalability
On the scalability of CFD tool for supersonic jet flow configurations
摘要：
新的法规正在对航空业的噪声排放进行限制，这促使研究人员和工程师投入精力研究航空声学现象。根据这一趋势，建立了一个内部计算流体动力学工具，以再现航空声学模拟应用中的超声速喷流的高保真度结果。求解器是使用大涡模拟公式，离散使用有限差分法和显式时间积分。超音速射流的数值模拟是非常昂贵的，需要高效的高性能计算。因此，非阻塞消息通道接口协议和并行输入/输出功能被实现到代码中，以执行需要多达10亿个网格点的模拟。目前的工作解决了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。不同的网格配置，其大小从几十万到大约十亿个网格点，在本文中进行了评估。使用不同的工作负载进行计算，以评估并行计算工具的强和弱的可扩展性。此外，一个现实的流动条件的验证结果也在目前的工作。
英文摘要：
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.
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