Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114 | Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca0012h-sa)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0012h-sa | 50,000 | 9 | 20.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0012h-sa | 50,000 | 5 | 22.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0012h-sa | 100,000 | 9 | 28.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0012h-sa | 100,000 | 5 | 33.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0012h-sa | 200,000 | 9 | 41.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0012h-sa | 200,000 | 5 | 46.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0012h-sa | 500,000 | 9 | 63.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0012h-sa | 500,000 | 5 | 66.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0012h-sa | 1,000,000 | 9 | 82 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0012h-sa | 1,000,000 | 5 | 81.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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