Aerodynamic Validation of the ONERA M6 Wing Using Transonic CFD Simulation

The ONERA M6 wing remains a cornerstone benchmark in transonic aerodynamics, essential for verifying the accuracy of numerical methods in predicting shock waves, three-dimensional flow phenomena, and shock-boundary-layer interactions. This study presents a Computational Fluid Dynamics (CFD) analysis of the ONERA M6 wing, aiming to validate numerical predictions against established reference data from NASA's Turbulence Modelling Resource. Simulations were conducted using ANSYS Fluent under transonic conditions, utilizing a density-based solver, paired with the Spalart-Allmaras turbulence model. Sutherland's law was applied to resolve temperature-dependent viscosity effects. The analysis focuses on critical aerodynamic parameters, including surface pressure distributions, pressure coefficient Cp profiles, shock topology, Mach number contours, and integrated lift and drag coefficients. Numerical results successfully captured the definitive transonic features of the wing, specifically shock formation and its impact on aerodynamic performance. Validation against reference trends demonstrates reasonable agreement, confirming the capability of the selected numerical setup to resolve complex threedimensional flow physics. Ultimately, this work serves as a robust validation exercise, reinforcing practical methodologies for transonic CFD simulations and benchmark-based aerodynamic analysis.