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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(e655-il) EPPLER 655 AIRFOIL | Eppler E655 sailplane airfoil Max thickness 17.3% at 37.3% chord Max camber 3.9% at 42.4% chord | Remove Airfoil details Airfoil plotter |
(e668-il) EPPLER 668 AIRFOIL | Eppler E668 sailplane airfoil Max thickness 13.9% at 37.3% chord Max camber 4% at 47.8% chord | Remove Airfoil details Airfoil plotter |
(e793-il) EPPLER 793 AIRFOIL | Eppler E793 general purpose airfoil (gyroflug speed canard canard) Max thickness 15.6% at 26.7% chord Max camber 4.2% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e655-il,e668-il,e793-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e655-il | 50,000 | 9 | 4.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 50,000 | 5 | 14.6 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 100,000 | 9 | 36.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 100,000 | 5 | 30.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 200,000 | 9 | 69.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 200,000 | 5 | 69.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 500,000 | 9 | 116.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 500,000 | 5 | 111.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 9 | 150.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 5 | 135.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 50,000 | 9 | 31 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 50,000 | 5 | 27 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 100,000 | 9 | 51.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 100,000 | 5 | 47.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 200,000 | 9 | 81.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 200,000 | 5 | 77.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 500,000 | 9 | 123 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 500,000 | 5 | 113.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e668-il | 1,000,000 | 9 | 155.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e668-il | 1,000,000 | 5 | 135.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e793-il | 50,000 | 9 | 9.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e793-il | 50,000 | 5 | 30.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e793-il | 100,000 | 9 | 43.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e793-il | 100,000 | 5 | 52.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e793-il | 200,000 | 9 | 69.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e793-il | 200,000 | 5 | 72.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e793-il | 500,000 | 9 | 102.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e793-il | 500,000 | 5 | 100.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e793-il | 1,000,000 | 9 | 129.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e793-il | 1,000,000 | 5 | 123 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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