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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(goe413-il) GOE 413 AIRFOIL | Gottingen 413 airfoil Max thickness 16.4% at 30% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca652415a05-il) NACA 65(2)-415 a=0.5 | NACA 65(2)-415 a=0.5 airfoil Max thickness 15% at 39.9% chord Max camber 3% at 45% chord | Remove Airfoil details Airfoil plotter |
(e220-il) E220 (11.48%) | Eppler E220 low Reynolds number airfoil Max thickness 11.5% at 33.1% chord Max camber 2.2% at 37.7% chord | Remove Airfoil details Airfoil plotter |
(goe400-il) GOE 400 AIRFOIL | Gottingen 400 airfoil Max thickness 6.1% at 20% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe413-il,naca652415a05-il,e220-il,goe400-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe413-il | 50,000 | 9 | 7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 50,000 | 5 | 23.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 100,000 | 9 | 47.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 100,000 | 5 | 52.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 200,000 | 9 | 75.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 200,000 | 5 | 74.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 500,000 | 9 | 108.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 500,000 | 5 | 98.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 1,000,000 | 9 | 130.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 1,000,000 | 5 | 107.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 50,000 | 9 | 20.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 50,000 | 5 | 18.9 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 100,000 | 9 | 33.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 100,000 | 5 | 37 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 200,000 | 9 | 74.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 200,000 | 5 | 73.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 500,000 | 9 | 113.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 500,000 | 5 | 100.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 1,000,000 | 9 | 134.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 1,000,000 | 5 | 121.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e220-il | 50,000 | 9 | 31.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e220-il | 50,000 | 5 | 31 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e220-il | 100,000 | 9 | 52.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e220-il | 100,000 | 5 | 52.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e220-il | 200,000 | 9 | 76 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e220-il | 200,000 | 5 | 72.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e220-il | 500,000 | 9 | 105.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e220-il | 500,000 | 5 | 94.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e220-il | 1,000,000 | 9 | 123.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e220-il | 1,000,000 | 5 | 97.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 50,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 9 | 59.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 100,000 | 5 | 61.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 9 | 81 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 200,000 | 5 | 79.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 9 | 109.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 500,000 | 5 | 88.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 9 | 126 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe400-il | 1,000,000 | 5 | 101.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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