NACA 4412. Trailing Edge Separation Analysis
This case compares Flow360 results for the NACA 4412 airfoil against reference data from the NASA TMR Workshop. The simulations are run at Mach 0.09, Reynolds number 1.52 million, and an angle of attack of 13.87 degrees using the SA, SA-RC, and SST turbulence models. Across all three models, Flow360 predictions agree closely with CFL3D and FUN3D reference results. The results are presented through a Cp distribution, velocity profiles near the trailing edge at selected slices, and comparisons of overall aerodynamic performance in terms of CD and CL.
External reference data
NASA Turbulence Modeling Resource — NACA 4412 trailing-edge separation
turbmodels.larc.nasa.gov/naca4412sep_val.html
turbmodels.larc.nasa.gov/naca4412sep_val.html
Validation plots
Comparison of Flow360 predictions against reference data. Click an image to expand.
Surface pressure coefficient by turbulence model
Velocity and turbulent shear profiles by turbulence model
Solver performance
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