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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(e226-il) E226 (10.19%) | Eppler E226 low Reynolds number airfoil Max thickness 10.2% at 31.3% chord Max camber 0.5% at 56.9% chord | Remove Airfoil details Airfoil plotter |
(goe802b-il) GOE 802 B AIRFOIL | Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(e636-il) EPPLER 636 AIRFOIL | Eppler E636 airfoil Max thickness 11.9% at 26.9% chord Max camber 3.2% at 22.9% chord | Remove Airfoil details Airfoil plotter |
(e635-il) EPPLER 635 AIRFOIL | Eppler E635 airfoil Max thickness 11.6% at 26.2% chord Max camber 2.9% at 22.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e226-il,goe802b-il,e636-il,e635-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e226-il | 50,000 | 9 | 30.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 50,000 | 5 | 32.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 100,000 | 9 | 45.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 100,000 | 5 | 44.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 200,000 | 9 | 59.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 200,000 | 5 | 55.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 500,000 | 9 | 77.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 500,000 | 5 | 67.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 1,000,000 | 9 | 86.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 1,000,000 | 5 | 73.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 50,000 | 9 | 26.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 50,000 | 5 | 39.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 9 | 53.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 5 | 60.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 9 | 76.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 5 | 73.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 9 | 104.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 9 | 105.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 5 | 103.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 50,000 | 9 | 14.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 50,000 | 5 | 24.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 100,000 | 9 | 33 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 100,000 | 5 | 44 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 200,000 | 9 | 61.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 500,000 | 9 | 95.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 500,000 | 5 | 94.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 9 | 120.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 5 | 108.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 50,000 | 9 | 14.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 50,000 | 5 | 24 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 100,000 | 9 | 36.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 100,000 | 5 | 43.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 200,000 | 9 | 60.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 200,000 | 5 | 64 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 500,000 | 9 | 92.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 500,000 | 5 | 88 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 9 | 113.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 5 | 100 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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