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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-3-cfd-and-validation/
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课程名称：ONERA M6翼的CFD分析 - 第三部分 CFD及验证 课程概述：在本课程中，您将学习关于ONERA M6翼的CFD分析。首先，我们将介绍问题描述及给定的操作条件。之后，我们将讨论不同的气动系数，例如升力系数及参考条件。我将解释如何根据雷诺数和马赫数计算参考面积、压力、密度等。接着，我们将讨论实验数据中的Cp图。我们还将查阅不同文献，探索CD、CL和CM，因为这些数据在AGARD于1979年发布的实验工作中并未提供。不过，幸运的是，NASA已发布不同求解器和网格类型下的高质量CFD数据，包括Cp、CL、CD和CM。因此，我们将使用NASA数据比较阻力、升力和俯仰力矩系数。在这些讨论之后，我们将把网格导入Fluent。网格在第二部分中已在ICEMCFD Hexa中创建。我们将设置边界条件、操作条件、材料属性、求解器类型、参考值、报告定义，最后初始化解决方案并运行仿真。一旦解决方案完全收敛，我们将提取Cp和气动系数，并与可用数据进行比较。最后，我将解释如何获取Cp图并将其导入Excel中。然后我会教您如何对轴和Cp数据进行无量纲化并在Excel中绘制图表。实验数据的Cp将绘制在同一图表中。我们将使用NASA的Cp图并与我们的CFD、AGARD的实验数据和Fluent的CFD数据在同一个图表中进行比较。ONERA M6是CFD验证的经典测试案例。尽管其几何形状简单，但流场涉及复杂的流动特征，如跨声速流（马赫数0.7 - 0.92）、冲击波和边界层分离等。ONERA M6翼由ONERA气动部门于1972年设计，作为研究三维高雷诺数流动的实验几何体。ONERA是一种后掠翼，具有半跨长度。这是没有扭转的M5翼的外部三分之一。 课程学习成果： 1. 在这个三部分课程结束时，学生将能够根据各种湍流模型和适当的Y+值，进行外部、粘性、可压缩流动的CFD仿真，特别是在跨声速条件下的三维几何体。 2. 学生将能理解和学习高保真CFD分析中的所有过程，如几何创建、网格划分、CFD设置、求解及后处理。 3. 学生将能够根据AGARD报告的实验数据验证CFD结果。 课程涵盖内容： - 在SolidWorks中生成几何体 - 使用ICEMCFD进行半球体的网格划分 - 网格导入、边界条件指定、材料属性、求解器设置、报告定义、混合初始化等 - 稳态、3D雷诺平均纳维-斯图克斯方程 - Spalart-Allmaras、K-Epsilon、剪切应力传输SST和过渡湍流模型 - 2阶向上风流方案 - 可压缩、隐式求解器 - 无滑壁、对称和压力远场边界条件 - 使用Fluent 2022 R1中的最新选项加速收敛 - 并行求解器 - 结果的后处理 - 根据升力和阻力系数进行结果验证与收敛性评估 课程资源： 1. 所有的幻灯片 2. AGARD报告 3. 包括几何、域、六面体网格、已解决案例和数据文件的所有文件，数据的Excel文件，气动外形坐标以及NASA的几何数据 问题设置： 本问题将解决翼的流动，考虑以下条件： - 自由流温度 = 288.15 K - 自由流马赫数 = 0.8395 - 攻角(AOA) = 3.06度 - 雷诺数 = 11.72E6 - 平均气动弦长 = 0.64607 m
In this course you will learn about CFD analysis of ONERA M6 wing. First we will go through problem descriptions and given operating conditions. After that we will discuss about the different aerodynamic coefficients such as lift coefficient and reference conditions. I will also explain that how to calculate reference area, pressure, density etc. from Reynolds number and Mach number. We will then discuss about the experimental data for Cp plots. We will then go through different literature to explore the CD, CL and CM as these are not given in experimental work by AGARD published in 1979. But fortunately NASA has published high quality CFD data for Cp and CL, CD and CM for different solvers and mesh types. Therefore we will use NASA data to compare drag, lift and pitching moment coefficients. After this all discussion we will import mesh into Fluent. Mesh is already created in ICEMCFD hexa in part 2. We will set boundary conditions, operating conditions, material properties, solver type, reference values, report definitions and finally we will initialize solution and run the simulation. Once solution is fully converged, we will extract Cp and aerodynamic coefficients. We will compare them with available data. Finally I will explain method to get Cp plot and import it into excel. Then I will teach you how to non dimensionalize axis and Cp data and plot it in excel. Experimental data for Cp will be plotted in same graph. We will use NASA Cp plot and plot it in same plot to compare our CFD, experimental data from AGARD and CFD data from Fluent. 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. 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 m
