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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(pw106-pw) PW106 | Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.9% at 27.5% chord Max camber 2.1% at 27.5% chord | Remove Airfoil details Airfoil plotter |
(naca66210-il) NACA 66-210 | NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (pw106-pw,naca66210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pw106-pw | 50,000 | 9 | 25 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 100,000 | 9 | 46.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 200,000 | 9 | 61.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 500,000 | 9 | 74.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 1,000,000 | 9 | 84.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 2,000,000 | 9 | 94.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 5,000,000 | 9 | 116.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 5 | 27.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 5 | 36.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 9 | 51.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 5 | 46.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 5 | 61.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 0 | 67.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 9 | 82.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 5 | 67.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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