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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(nacam12-il) NACA M12 | NACA M12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(rhodesg32-il) Rhode St. Genese 32 | Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% 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 |
(n64015-il) NACA 642-015 AIRFOIL | NACA 64(2)-015 airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nacam12-il,rhodesg32-il,fauvel-il,n64015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam12-il | 50,000 | 9 | 31.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 100,000 | 9 | 49.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 100,000 | 5 | 48.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 200,000 | 9 | 66.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 200,000 | 5 | 56.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 500,000 | 9 | 71.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 500,000 | 5 | 62.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam12-il | 1,000,000 | 9 | 78.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam12-il | 1,000,000 | 5 | 71.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 9 | 24.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 5 | 33.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 9 | 45.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 5 | 48.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 9 | 64.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 5 | 64.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 5 | 89.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 9 | 115 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 5 | 108 at α=4.25° | 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 | |
| n64015-il | 50,000 | 9 | 27.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015-il | 50,000 | 5 | 27 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015-il | 100,000 | 9 | 40.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015-il | 100,000 | 5 | 35.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015-il | 200,000 | 9 | 48.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015-il | 200,000 | 5 | 45 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015-il | 500,000 | 9 | 65.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015-il | 500,000 | 5 | 52.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015-il | 1,000,000 | 9 | 72.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015-il | 1,000,000 | 5 | 65 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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