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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(e330-il) EPPLER 330 AIRFOIL | Eppler E330 flying wing airfoil Max thickness 11% at 29.2% chord Max camber 2.1% at 16.9% 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 |
(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 |
(e209-il) E209 (13.72%) | Eppler E209 low Reynolds number airfoil Max thickness 13.7% at 33.8% chord Max camber 1.6% at 48.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e330-il,e668-il,e662-il,e209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e330-il | 50,000 | 9 | 17.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e330-il | 50,000 | 5 | 26.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e330-il | 100,000 | 9 | 40.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e330-il | 100,000 | 5 | 44.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e330-il | 200,000 | 9 | 60.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e330-il | 200,000 | 5 | 61.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e330-il | 500,000 | 9 | 85.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e330-il | 500,000 | 5 | 71.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e330-il | 1,000,000 | 9 | 89.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e330-il | 1,000,000 | 5 | 84.8 at α=8° | 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 | |
| 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 | |
| e209-il | 50,000 | 9 | 29.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 50,000 | 5 | 31.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 100,000 | 9 | 50.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 100,000 | 5 | 51.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 200,000 | 9 | 71.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 200,000 | 5 | 69.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 500,000 | 9 | 100.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 500,000 | 5 | 93 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 1,000,000 | 9 | 121.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 1,000,000 | 5 | 103.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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