CFD analysis of ONERA M6 wing – Part 3 CFD and validation

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

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 Spaceclaim

• Hexa meshing in ICEMCFD

• Mesh import, boundary conditions specification, material properties, solver settings, report definitions, hybrid initialization etc.

• Steady state, 3D Reynolds-Averaged Navier-Stokes

• Spalart-Allmaras, K-Epislon, Shear Stress Transport SST and transition turbulence models

• 2nd order upwind flow scheme

• Compressible, implicit solver

• No slips wall, Symmetry and pressure Far-Field boundary conditions

• Convergence acceleration using latest options in Fluent 2022 R1

• Parallel 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 Setup

This problem will solve the flow past the wing with these conditions:

• Freestream Temperature = 288.15 K

• Freestream Mach number = 0.8395

• Angle of attack (AOA) = 3.06 deg

• Reynolds number = 11.72E6

• Mean aerodynamics chord = 0.64607 m

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