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所在平台: Udemy |
课程主页: https://www.udemy.com/course/cfd-analysis-of-onera-m6-wing-part-1-geometry-modeling/
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Coursera CFD分析 ONERA M6 机翼 - 第一部分 几何建模 课程总结： 本课程是 ONERA M6 机翼 CFD 分析系列课程的第一部分，旨在教授学员如何进行该经典验证案例的几何建模。ONERA M6 机翼是一个用于研究三维、高雷诺数流动的实验几何体，其特点是具有复杂的跨音速流动特征，如激波和边界层分离。 **课程目标：** * 在 Coursera 的这三部分课程结束后，学员将能够： 1. 针对三维几何体在跨音速条件下，使用多种湍流模型和合适的 Y+ 值，执行外部粘性可压缩流动的 CFD 模拟。 2. 理解并掌握高保真 CFD 分析的全部流程，包括几何创建、网格划分、CFD 设置、求解和后处理。 3. 根据 AGARD 报告中的实验数据验证 CFD 结果。 **本课程（第一部分）内容：** * **几何建模：** 使用 SolidWorks 创建 ONERA M6 机翼的几何模型。 * **域创建：** 在 SpaceClaim 中根据 AGARD AR 138 报告的要求，创建计算域。 **后续课程（第二、三部分）将涵盖：** * **第二部分：** 在 ICEM CFD 中为 ONERA M6 机翼创建高质量的六面体网格，重点关注边界层和激波的解析。 * **第三部分：** 在 Fluent 中进行高质量的 CFD 分析，并对升力、阻力系数以及不同展向位置的压差系数等数据进行后处理和验证。 **将涵盖的详细主题：** * SolidWorks 中的几何生成 * Spaceclaim 中的半球形域创建 * ICEM CFD 中的六面体网格划分 * 网格导入 * 边界条件设定 * 材料属性 * 求解器设置 * 报告定义 * 混合初始化 * 稳态、三维雷诺平均纳维-斯托克斯方程 * Spalart-Allmaras, K-Epsilon, SST 剪切应力传输以及过渡湍流模型 * 二阶迎风流动格式 * 可压缩、隐式求解器 * 无滑移壁面、对称性和远场压力边界条件 * 使用 Fluent 2022 R1 的最新选项进行收敛加速 * 并行求解器 * 结果后处理 * 与实验数据的验证 * 基于升力和阻力系数的收敛性评估 **课程资源：** 学员将获得所有 PowerPoint 幻灯片、AGARD 报告、以及包含几何模型、计算域、六面体网格、已求解的计算案例和数据文件、用于数据分析的 Excel 文件、翼型坐标以及来自 NASA 的几何模型等所有相关文件。 **问题设定：** 本次模拟将处理以下流场条件下的 ONERA M6 机翼流动： * 自由流温度：288.15 K * 自由流马赫数：0.8395 * 迎角 (AOA)：3.06 度 * 雷诺数：11.72 x 10^6 * 平均空气动力学弦长：0.64607 m 这些跨音速流动条件将导致机翼上表面出现典型的“lambda”激波。
ONERA M6 is a classical test case for CFD validation. Although geometry is simple, but the flow field involves complex flow features such as transonic flow (Mach No. 0.7 - 0.92) with shocks, boundary layer separation etc. The ONERA M6 wing was designed in 1972 by the ONERA Aerodynamics Department as an experimental geometry for studying three-dimensional, high Reynolds number flows. ONERA is a swept back wing, with half span. It is external third of M5 Wing without twist. In this three part course series, you will learn about the conducting CFD analysis of ONERA M6 wing as per data given by AGARD AR 138 1979 by Schmitt, V. and F. Charpin. Part 1 (Present course) deals with geometry modeling in solidworks and domain creation in spacelaim according to above reference. Part 2 will teach to create high quality hexa meshing for the same wing in ICEMCFD. With consideration to resolve boundary layer and shock wave. Third part will teach you about conducting high quality CFD analysis in Fluent and post processing of data such as lift and drag coefficient. And also coefficient of pressure at various span locations. Learning outcomes of this course: 1. At the end of this three part course/tutorial, student will be able to perform CFD simulation of exteneral, viscous, compressible flow around 3D geometry at transonic conditions using various turbulence models and appropriate Y+ values. 2. Student will be able to understand/learn all processes involved in high fidelity CFD analysis such as geometry creation, meshing, CFD setup, solution and post processing. 3. Student will be able to validate CFD results against experimental data from AGARD report. 4. Following things will be covered: Geometry generation in Solidworks Hemisphere domain in SpaceclaimHexa meshing in ICEMCFDMesh import, boundary conditions specification, material properties, solver settings, report definitions, hybrid initialization etc. Steady state, 3D Reynolds-Averaged Navier-StokesSpalart-Allmaras, K-Epislon, Shear Stress Transport SST and transition turbulence models2nd order upwind flow scheme Compressible, implicit solver No slips wall, Symmetry and pressure Far-Field boundary conditionsConvergence acceleration using latest options in Fluent 2022 R1Parallel solver Post processing of results Validations of results against experimental data. solution convergence assessment based on lift and drag coefficients. Resources: You will get following resources in this course 1. All power point slides 2. AGARD Report 3. All files including geometry, domain, hexa mesh, solved case and data files, excel file for data, aerofoil coordinates and also geometry from NASA. Problem SetupThis problem will solve the flow past the wing with these conditions:Freestream Temperature = 288.15 KFreestream Mach number = 0.8395Angle of attack (AOA) = 3.06 degReynolds number = 11.72E6Mean aerodynamics chord = 0.64607 mThese transonic flow conditions will cause the typical "lambda" shock along the upper surface of the lifting wing.
