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 |
(goe101-il) GOE 101 AIRFOIL | Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
(e58-il) EPPLER 58 AIRFOIL | Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe363-il) GOE 363 AIRFOIL | Gottingen 363 airfoil Max thickness 11.1% at 19.8% chord Max camber 5.7% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(e654-il) EPPLER 654 AIRFOIL | Eppler E654 sailplane airfoil Max thickness 17.2% at 36.1% chord Max camber 4.9% at 46.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nacam12-il,goe101-il,e58-il,goe363-il,e654-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 | |
| goe101-il | 50,000 | 9 | 39.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 50,000 | 5 | 41.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 9 | 58.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 100,000 | 5 | 59.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 9 | 77.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 200,000 | 5 | 77.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 9 | 104.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 500,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 9 | 123.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe101-il | 1,000,000 | 5 | 114.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 50,000 | 9 | 46.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 50,000 | 5 | 44.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 100,000 | 9 | 70.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 100,000 | 5 | 68.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 200,000 | 9 | 108.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 200,000 | 5 | 106.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 500,000 | 9 | 175.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 500,000 | 5 | 166.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 9 | 235.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 5 | 160.8 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe363-il | 50,000 | 9 | 32.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe363-il | 50,000 | 5 | 37 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe363-il | 100,000 | 9 | 53.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe363-il | 100,000 | 5 | 52.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe363-il | 200,000 | 9 | 70.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe363-il | 200,000 | 5 | 65.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe363-il | 500,000 | 9 | 89.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe363-il | 500,000 | 5 | 88.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe363-il | 1,000,000 | 9 | 110.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe363-il | 1,000,000 | 5 | 104.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 50,000 | 9 | 5.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 50,000 | 5 | 12.8 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 100,000 | 9 | 32.7 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 100,000 | 5 | 28.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 200,000 | 9 | 70.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 500,000 | 9 | 122.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 500,000 | 5 | 118 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 1,000,000 | 9 | 158.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 1,000,000 | 5 | 145.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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