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Towards a Unified K-Epsilon Turbulence Model for the Practical Analysis of Aeropropulsive Flows

机译:建立统一的K-Epsilon湍流模型,用于实际分析航空推进流

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While LES-based methods are starting to be used more routinely for analyzing complex aero-propulsive flows, their routine use for design/optimization and systems studies, where numerous solutions must be generated in a "production-line" manner, remains a future goal requiring more robust computer resources and advances in LES methodology. A Reynolds Averaged Navier-Stokes (RANS) approach currently provides the most viable option for performing fast-paced industrial/engineering studies, with a principal drawback being the accuracy and reliability of the turbulence models used, which often struggle to accurately capture the physics for more complex flow without resorting to highly specialized extensions. Progress made towards developing a unified RANS k-epsilon turbulence model, shown to accurately analyze a variety of high-speed aero-propulsive problems without problem specific model tuning or user intervention is described in this paper. This has entailed: including generalized corrections for compressibility and baroclinic torque; accounting for variations in turbulent Prandtl and Schmidt numbers; and employing an adaptive approach to locally implement non-linear modeling extensions. This paper will describe several simulations where turbulence model extensions have provided improvements in comparison to data, and will also discuss areas where improving the model's performance requires further work. Improving the unified model will be guided to some extent by comparisons with data, but more so by comparisons with LES/DNS based solutions shown to adequately analyze problem sets for which the RANS model has had limited success. In a companion paper at this meeting, DES-based solutions being used to support upgrades to the RANS model, are described. The DES model uses this unified RANS model for wall bounded and interfacing regions and can thus deal with not only conventional turbulence model interfacing, but with the interfacing of scalar fluctuations.
机译:尽管基于LES的方法开始被越来越多地用于分析复杂的航空推进流,但是它们的常规设计/优化和系统研究却必须以“生产线”的方式产生众多解决方案,这仍然是未来的目标需要更强大的计算机资源和LES方法的进步。目前,雷诺平均Navier-Stokes(RANS)方法为进行快节奏的工业/工程研究提供了最可行的选择,主要缺点是所用湍流模型的准确性和可靠性,而湍流模型通常难以准确地捕获物理场。更复杂的流程,而无需求助于高度专业化的扩展。本文描述了开发统一的RANSk-ε湍流模型所取得的进展,该模型可准确地分析各种高速航空推进问题,而无需进行特定问题的模型调整或用户干预。这需要:包括对可压缩性和斜压扭矩的广义校正;解释湍流的Prandtl和Schmidt数的变化;并采用一种自适应方法来本地实现非线性建模扩展。本文将描述几种湍流模型扩展相对于数据提供了改进的模拟,还将讨论在改进模型性能方面需要进一步工作的领域。通过与数据进行比较,可以在某种程度上指导改进统一模型,但是,通过与基于LES / DNS的解决方案进行比较,可以更好地指导统一模型,该解决方案可以充分分析RANS模型在成功方面有限的问题集。在本次会议的配套文件中,描述了用于支持RANS模型升级的基于DES的解决方案。 DES模型将这种统一的RANS模型用于墙的边界区域和界面区域,因此不仅可以处理常规湍流模型的界面,还可以处理标量波动的界面。

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