ONERA M6 Wing. Transonic Grid Convergence Study
The ONERA M6 wing is a canonical transonic CFD validation case: a 30-degree swept, semi-span wing with a symmetric ONERA D airfoil section that develops a characteristic lambda shock on the upper surface, supported by classical wind-tunnel data and a multi-code NASA TMR grid-convergence study. Conditions are Mach 0.84, Reynolds number 11.72 million based on mean aerodynamic chord, and 3.06 degrees angle of attack. Four mesh refinement levels (coarse through extra-fine) are taken from the NASA Turbulence Modeling Resource ONERA M6 grid family and solved with the Spalart-Allmaras turbulence model. Grid convergence of integrated forces is assessed against reference CFD results. Surface pressure and skin friction distributions are compared against reference CFD data (FUN3D) and experiment.
tmbwg.github.io/turbmodels/onerawingnumerics_val.html
Comparison of Flow360 predictions against reference data. Click an image to expand.
