Published 11/2022
MP4 | Video: h264, 1280x720 | Audio: AAC, 44.1 KHz
Language: English | Size: 1.71 GB | Duration: 2h 18m

CFD analysis of ONERA M6 wing using Fluent and validation with AGARD experimental data and high quality CFD from NASA

What you'll learn
To conduct CFD analysis of ONERA M6 wing in particular and CFD analysis of any wing or aerodynamic body in general
How to get high quality data from literature for validation
Understanding drag, lift and pitching moment coefficient and reference values
Setting up problem in Fluent and accelerating convergence
Effect of turbulence model and Y+ values on aerodynamic coefficient
Validating present CFD with avaiable experimental data and high quality CFD from NASA
Effect of different solvers on results
Requirements
Basic understanding of aerodynamics and CFD
Should be able to use Fluent on basic level
Computer with i3 or better processor and 8 GB RAM. 16 GB RAM is recommended
ANSYS 2022 R1 installed on your computer
Description
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
Overview
Section 1: Introduction
Lecture 1 Introduction
Lecture 2 Problem description
Lecture 3 Aerodynamic coefficients e.g. drag coefficient and reference quantities
Section 2: Solving ONERA M6 wing in Fluent 2022 R1
Lecture 4 Importing mesh, computational settings and solving
Lecture 5 Getting drag coefficients etc from CFD and comparing with available data
Lecture 6 Computing Cp and comparing with experimental data and CFD from NASA
Section 3: Density and pressure based solver comparison
Lecture 7 Effect of pressure and density based solver on results
Students pursuing career in mechanical or aerospace engineering,Processionals who want to enhance their CFD skills to advanced level,Any CFD enthusiast who want to expand his skill level


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