Cfd Analysis Of Onera M6 Wing - Part 2 Hexa Meshing

High quality hexa meshing of ONERA M6 for most accurate and authentic results for CFD validation

What you'll learn
Importing files into ICEMCFD
Thinking about the grid toplogy
creating hexa mesh
creating three meshes
Requirements
Basic understanding of CFD and mesh generation in ICEMCFD
ANSYS 2022 R1 professional installed on your computer
Computer with i5/i7 CPU and atleast 8 GB RAM
Description
In this course you will learn about hexa meshing of ONERA M6 wing. In first part we have made geometry of ONERA M6 wing in Solidworks and now same geometry will used for making the grid. 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

Overview

Section 1: Introduction

Lecture 1 Introduction

Section 2: Hexa mesh generation in ICEMCFD

Lecture 2 Geometry import and some preliminary settings

Lecture 3 Discussion on Grid Topology for ONERA M6 Wing and creating master block

Lecture 4 Splitting block into smaller blocks and adjusting it for wing

Lecture 5 General adjustment of blocking for outer most edges and vertices

Lecture 6 Preliminary mesh settings and further adjustments to blocking

Lecture 7 O-Grid around wing for boundary layer

Lecture 8 Refining mesh in O-Grid

Lecture 9 Creating 2nd O-Grid in trailing edge region

Lecture 10 Refining and improving mesh in whole domain

Lecture 11 Solving low quality mesh issues to improve minimum quality and min angle

Lecture 12 Preparing final mesh ready for simulation

Lecture 13 Exporting mesh

Interested in learning CFD analysis of wings