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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(e662-il) EPPLER E662 AIRFOIL | Eppler E662 sailplane airfoil Max thickness 15% at 42.8% chord Max camber 4.1% at 47.5% chord | Remove Airfoil details Airfoil plotter |
(e335-il) EPPLER 335 AIRFOIL | Eppler E335 flying wing airfoil Max thickness 12.6% at 29% chord Max camber 2.3% at 19.9% 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 |
(e228-il) E10(08%) | Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord | Remove Airfoil details Airfoil plotter |
(e205-il) E205 (10.48%) | Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% 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 |
(e66-il) EPPLER 66 AIRFOIL | Eppler E66 low Reynolds number airfoil Max thickness 10.1% at 28.7% chord Max camber 4.1% at 52.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e662-il,e335-il,e220-il,e228-il,e205-il,e654-il,e66-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e662-il | 50,000 | 9 | 27.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 50,000 | 5 | 23.4 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 100,000 | 9 | 46.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 100,000 | 5 | 40.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 200,000 | 9 | 71.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 200,000 | 5 | 66.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 500,000 | 9 | 114.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 500,000 | 5 | 111.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 9 | 152 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 5 | 138.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 50,000 | 9 | 15.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 50,000 | 5 | 25.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 100,000 | 9 | 38.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 100,000 | 5 | 44.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 200,000 | 9 | 60.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 200,000 | 5 | 58.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 500,000 | 9 | 81.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 500,000 | 5 | 72 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 9 | 90.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 5 | 88.7 at α=8.75° | 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 | |
| e228-il | 50,000 | 9 | 27 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 50,000 | 5 | 28.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 100,000 | 9 | 39.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 100,000 | 5 | 38.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 200,000 | 9 | 51.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 200,000 | 5 | 48.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 500,000 | 9 | 66.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 500,000 | 5 | 61.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 1,000,000 | 9 | 75.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 1,000,000 | 5 | 71.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 50,000 | 9 | 32.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 50,000 | 5 | 34.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 100,000 | 9 | 53.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 100,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 200,000 | 9 | 75.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 200,000 | 5 | 74 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 500,000 | 9 | 105.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 500,000 | 5 | 98.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 9 | 128.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e205-il | 1,000,000 | 5 | 116.5 at α=5° | 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 | |
| e66-il | 50,000 | 9 | 40.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 50,000 | 5 | 40.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 100,000 | 9 | 64.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 100,000 | 5 | 63.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 200,000 | 9 | 91.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 200,000 | 5 | 86.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 500,000 | 9 | 128.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 500,000 | 5 | 113.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 9 | 153.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 5 | 121.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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