CFD analysis of ONERA M6 wing - Part 1 Geometry modeling

Description

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 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

  
  

These transonic flow conditions will cause the typical “lambda” shock along the upper surface of the lifting wing.

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