NACA 0012 Airfoil. Symmetric Airfoil Validation
This case evaluates Flow360 on the NACA 0012 airfoil from the NASA Turbulence Modeling Resource at Mach 0.15 and Reynolds number 6.0e6. The primary purpose of this study is to validate Flow360 for a fundamental airfoil flow across 3 angles of attack using different turbulence models. The runs cover angles of attack of 0, 10, and 15 degrees using the SA, SA-RC, and SST turbulence models. The lift polar and surface-pressure distributions are compared against available experimental data and results from other CFD codes on the same workshop mesh.
External reference data
NASA Turbulence Modeling Resource, NACA 0012 Airfoil Validation Case
tmbwg.github.io/turbmodels/naca0012_val.html
tmbwg.github.io/turbmodels/naca0012_val.html
Validation plots
Comparison of Flow360 predictions against reference data. Click an image to expand.
Lift coefficient by turbulence model and angle of attack
Drag polar by turbulence model
Surface pressure by turbulence model and angle of attack
Solver performance
Request access