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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(goe367-il) GOE 367 AIRFOIL | Gottingen 367 airfoil Max thickness 16.3% at 29.7% chord Max camber 4.6% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(e585-il) EPPLER 585 AIRFOIL | Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord | Remove Airfoil details Airfoil plotter |
(e266-il) EPPLER 266 AIRFOIL | Eppler E266 general purpose airfoil Max thickness 17.3% at 39.8% chord Max camber 3.1% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(pt40-il) PT40 | Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe367-il,e585-il,e266-il,pt40-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe367-il | 50,000 | 9 | 5.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 9 | 68 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 5 | 64.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 9 | 93.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 9 | 111.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 5 | 98.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 50,000 | 9 | 8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 50,000 | 5 | 21.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 100,000 | 5 | 47.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 200,000 | 9 | 81.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 200,000 | 5 | 78.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 500,000 | 9 | 118 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 500,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 9 | 146.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 5 | 131.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 50,000 | 9 | 13.9 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 50,000 | 5 | 13.4 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 100,000 | 9 | 26 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 100,000 | 5 | 23.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 200,000 | 9 | 61.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 200,000 | 5 | 59.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 500,000 | 9 | 100.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 500,000 | 5 | 100 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 9 | 131.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 5 | 124.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 9 | 32.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 9 | 48.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 5 | 46.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 9 | 64.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 9 | 78.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 9 | 95 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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