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

Unlock the secrets of transonic aerodynamics with this comprehensive CFD course, focusing on the ONERA M6 wing. This three-part series provides a deep dive into simulating complex flow phenomena around a classic wing geometry, validated against real-world experimental data.

What You'll Learn:

• CFD Analysis of the ONERA M6 Wing: Master the process of conducting CFD simulations for external, viscous, and compressible flows at transonic conditions (Mach 0.7 - 0.92).
• Aerodynamic Coefficients: Understand and calculate crucial aerodynamic coefficients like lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM). Learn how to determine reference area, pressure, density, and more from Reynolds and Mach numbers.
• Turbulence Modeling: Explore various turbulence models including SST (Shear Stress Transport), K-Epsilon, and Spalart-Allmaras to accurately simulate complex flow features like boundary layer separation and shocks.
• Mesh Generation: Learn to create a high-quality hexa mesh using ICEMCFD (part 2 of the course).
• CFD Setup in Fluent: Gain hands-on experience with ANSYS Fluent 2022 R1, covering:
  • Boundary condition specification (no-slip wall, symmetry, far-field)
  • Material properties
  • Solver settings (compressible, implicit solver)
  • Report definitions
  • Hybrid initialization
  • Convergence acceleration techniques
• Post-Processing & Validation: Extract and analyze Cp (pressure coefficient) plots and aerodynamic coefficients. Validate your CFD results against experimental data from the AGARD AR 138 1979 report by Schmitt and Charpin, and compare with high-quality CFD data from NASA.
• Non-Dimensionalization & Visualization: Learn to non-dimensionalize axis and Cp data for clear and insightful analysis, including plotting against experimental data in Excel.
• Geometry Creation & Meshing: Understand geometry generation in Solidworks and meshing in Spaceclaim for creating the domain and hexa mesh.

The ONERA M6: A Challenging Test Case

The ONERA M6 wing, designed in 1972, is a swept-back, half-span wing representing the external third of the M5 wing without twist. It's a benchmark for CFD validation due to its complex flow field, including transonic flow, shocks, and boundary layer separation.

Learning Outcomes:

• Perform CFD simulations of external, viscous, compressible flow around 3D geometries at transonic conditions.
• Understand the entire CFD analysis workflow: geometry creation, meshing, setup, solution, and post-processing.
• Validate CFD results against experimental data from the AGARD report.
• Master key CFD techniques: mesh import, boundary conditions, solver settings, convergence assessment.

Resources Included:

• All PowerPoint slides
• AGARD Report
• Geometry, domain, mesh, solved case, data files, Excel file, airfoil coordinates, and NASA geometry.

Problem Setup:

This course will focus on the following operating conditions:

• Freestream Temperature: 288.15 K
• Freestream Mach Number: 0.8395
• Angle of Attack (AOA): 3.06 degrees
• Reynolds Number: 11.72E6
• Mean Aerodynamic Chord: 0.64607 m

This course is ideal for students and engineers looking to develop expertise in CFD simulation, aerodynamics, and transonic flow analysis.