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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(naca22112-jf) NACA 22112 | NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord | Remove Airfoil details Airfoil plotter |
(fauvel-il) FAUVEL 14% AIRFOIL | Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca22112-jf,fauvel-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca22112-jf | 50,000 | 9 | 23.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 50,000 | 5 | 26.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 100,000 | 9 | 33.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 100,000 | 5 | 36.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 200,000 | 9 | 45.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 200,000 | 5 | 49.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 500,000 | 9 | 67.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 500,000 | 5 | 71.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 1,000,000 | 9 | 89.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 1,000,000 | 5 | 89.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 50,000 | 9 | 9.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 50,000 | 5 | 18.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 100,000 | 9 | 22.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 100,000 | 5 | 39.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 200,000 | 9 | 57.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 200,000 | 5 | 60.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 500,000 | 9 | 89.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 500,000 | 5 | 82.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 1,000,000 | 9 | 106.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 1,000,000 | 5 | 96 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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