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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(e333-il) EPPLER 333 AIRFOIL | Eppler E333 flying wing airfoil Max thickness 11.7% at 31.3% chord Max camber 3.5% at 26.4% chord | Remove Airfoil details Airfoil plotter |
(e224-il) E224 (10.17%) | Eppler E224 low Reynolds number airfoil Max thickness 10.2% at 29.8% chord Max camber 1.5% at 54.2% chord | Remove Airfoil details Airfoil plotter |
(e434-il) EPPLER 434 AIRFOIL | Eppler E434 sailplane airfoil Max thickness 13.3% at 38.6% chord Max camber 4.3% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e333-il,e224-il,e434-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e333-il | 50,000 | 9 | 17.4 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 50,000 | 5 | 27.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 100,000 | 9 | 40.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 100,000 | 5 | 48 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 200,000 | 9 | 65.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 200,000 | 5 | 68.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 500,000 | 9 | 99.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 500,000 | 5 | 92.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 1,000,000 | 9 | 117.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 1,000,000 | 5 | 109.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 50,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 50,000 | 5 | 35.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 200,000 | 9 | 68.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 200,000 | 5 | 63.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 500,000 | 9 | 89.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 500,000 | 5 | 79.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 9 | 102.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e434-il | 50,000 | 9 | 8.6 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e434-il | 50,000 | 5 | 23.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e434-il | 100,000 | 9 | 52.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e434-il | 100,000 | 5 | 50.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e434-il | 200,000 | 9 | 82 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e434-il | 200,000 | 5 | 80.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e434-il | 500,000 | 9 | 122 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e434-il | 500,000 | 5 | 109.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e434-il | 1,000,000 | 9 | 145.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e434-il | 1,000,000 | 5 | 128.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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