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所在平台: Udemy |
课程主页: https://www.udemy.com/course/absolute-beginners-guide-to-cfd-simulation-in-ansys/
课程评论：没有评论
Course Title: ANSYS CFD 仿真入门指南 (Absolute Beginners Guide to CFD simulation in ANSYS) Course Summary: 本课程将指导您从零开始进行首次CFD (计算流体动力学) 仿真。我们将以波音747-400简化模型为案例，学习ANSYS Workbench中的重要CFD模块。 课程内容概述： 1. **几何处理与域创建 (ANSYS Spaceclaim)**：学习使用ANSYS Spaceclaim进行几何清理，并为波音747-400全模型创建仿真域。同时，将创建“影响体”(Body of Influence, BOI)，用于在尾流区域进行网格细化。 2. **网格生成 (ANSYS Workbench Grid Generation)**：使用相同的几何体和仿真域，在Workbench网格生成器中创建混合网格。我们将生成棱柱层以捕捉边界层流动特征（对气动流动至关重要），并利用影响体在尾流区域实现网格细化。 3. **仿真设置 (ANSYS Fluent)**： * **流动设置**：配置可压缩流动仿真，包括设置适当的缩放因子，选择合适的湍流模型，启用能量方程，以及使用理想气体定律定义密度。 * **边界条件**：定义关键的边界条件，特别是进口条件（以马赫数表示）。 * **参考条件**：设置参考条件，包括参考面积和参考长度。 * **报告定义**：设置报告定义，用于监测阻力系数 (Cd) 和升力系数 (Cl) 的变化。 * **求解器设置**：初始化求解（使用混合方法），并利用Fluent的“求解器引导”(Solution Steering) 功能加速收敛。 4. **仿真运行与分析**： * 运行仿真，直到阻力系数和升力系数的收敛图显示结果稳定。 * **后处理**：分析流场，包括压力系数 (Cp) 图、矢量图、压力和马赫数云图，并绘制流线图以观察流动与飞机表面的相互作用。 * 最终计算并得出阻力系数和升力系数。 5. **几何修改与结果比对**： * 将飞机的迎角 (Angle of Attack, AoA) 修改为8度。 * 快速更新网格，采用与零迎角情况相同的设置，并在Fluent中重新运行仿真。 * 对比零迎角和8度迎角情况下的仿真结果，讨论差异。 通过本课程，您将掌握使用ANSYS软件进行完整CFD仿真的基本流程和关键技术。
In this course you will learn your first CFD simulation from scratch. We will use Boeing 747-400 simplified model to learn important CFD modules in ANSYS workbench. We will use ANSYS Spaceclaim for geometry cleaning and creating domain for full Aircraft (Boeing 747-400). We will also crate body that will be used as body of influence (BOI) for mesh refinement in wake region. After that using same geometry and domain, we will cerate hybrid mesh in Workbench Grid generation app. We will create prism layers for capturing boundary layer flow features which are very important for aerodynamic flows such in our case. We will also refine mesh in wake using body of influence (BOI). This mesh will be then used for setting up compressible flow simulation in ANSYS Fluent. You will provide proper scaling factor, choosing appropriate turbulence model, enabling energy equation, using ideal gas las for density, defining boundary conditions specially at inlet in terms of Mach number, defining reference condition including reference area and reference length. You will also setup defining report definitions for monitoring drag and lift coefficients. Solution will be initialized using hybrid method. We will also setup solver so that we can accelerate solution convergence using "solution steering" option in Fluent. Finally we will hit the calculate option to solve CFD simulation using iterative solver schemes available in ANSYS Fluent. Once solution is converged based on plots of Cd and CL then we will analyze the flow field including Cp plot, vectors plots, contours plots for pressure and Mach number. We will also draw path lines to see how flow is interacting with Aircraft body. Finally we will find out drag and lift coefficients. Once more interesting part of this course is that, you will also modify the geometry of whole aircraft by providing angle of attack of 8 deg to full model. You will quickly update the mesh using settings for the pervious case with zero angle of attack (AoA), and run simulation in Fluent. We will again solve the problem in Fluent and discuss the differences in results as comparison to case with zero AoA.
