A unified modeling paradigm for turbulence, shock waves and boundary layers in computational compressible aerodynamics

计算可压缩空气动力学中湍流、冲击波和边界层的统一建模范例

• 批准号: 462115963
• 负责人: Dr. Marco ten Eikelder
• 金额: --
• 依托单位: Fachgebiet Numerische Mechanik
• 依托单位国家: 德国
• 项目类别: WBP Position
• 财政年份: 2021
• 资助国家: 德国
• 起止时间: 2020-12-31 至 2022-12-31
• 项目状态: 已结题
• 来源: https://gepris.dfg.de/gepris/projekt/462115963?language=en
• 关键词: unified; modeling; paradigm; turbulence; shock

Highly accurate computer simulations of compressible flows require methods for the reliable modeling of turbulence, shock waves and boundary layers. Existing modeling approaches achieve good results when simulating every single phenomenon on its own, but they interact with each other in an undesirable manner when turbulence, shock waves and boundary layers occur together. For example, numerical methods based on artificial viscosity for treating shock waves often influence the turbulence model in such a way that the simulation result becomes unphysical. The proposed project is based on the hypothesis that an integrated approach that considers the modeling of all three phenomena together can significantly improve the simulation accuracy of turbulent compressible flows. In the context of the finite element method the variational multiscale method (VMS) constitutes a promising tool for the simulation of turbulent compressible flows, in which practical mesh widths cannot resolve sharp interior and boundary layers as well as tiny turbulent eddies. The aim of the proposed project is to develop a unified VMS-based modeling approach for turbulence, shock waves and boundary layers that is based on the underlying entropy structure of the physical model and avoids any ad hoc mechanisms. The unified modeling approach to be developed will be integrated into modern discretization techniques based on higher-order isogeometric finite element methods. Its performance in terms of accuracy and robustness and its potential for use in industrial applications will be investigated and demonstrated using challenging aerodynamic simulation problems from aircraft and turbine design.

可压缩流的高精度计算机模拟需要湍流、激波和边界层的可靠建模方法。现有的建模方法在单独模拟每一种现象时都能取得很好的效果，但当湍流、冲击波和边界层同时发生时，它们会以不期望的方式相互作用。例如，用于处理激波的基于人工粘性的数值方法经常以这样的方式影响湍流模型，使得模拟结果变得非物理的。所提出的项目是基于这样的假设，即一个综合的方法，认为所有三种现象的建模在一起，可以显着提高湍流可压缩流的模拟精度。变分多尺度方法（VMS）的有限元方法的背景下，构成了一个很有前途的工具，用于模拟湍流可压缩流，其中实际的网格宽度不能解决尖锐的内部和边界层以及微小的湍流涡流。拟议项目的目的是开发一个统一的基于VMS的湍流，冲击波和边界层的建模方法，是基于物理模型的基本熵结构，并避免任何特设机制。统一建模方法将被开发集成到现代离散技术的基础上高阶等几何有限元方法。它在精度和鲁棒性方面的性能及其在工业应用中的潜力将通过飞机和涡轮机设计中具有挑战性的空气动力学模拟问题进行研究和演示。