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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(e853-il) EPPLER E853 AIRFOIL | Eppler E853 propeller airfoil Max thickness 11.6% at 37.1% chord Max camber 3.1% at 56.1% chord | Remove Airfoil details Airfoil plotter |
(e67-il) EPPLER 67 AIRFOIL | Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord Max camber 3.7% at 51.6% chord | Remove Airfoil details Airfoil plotter |
(e68-il) EPPLER 68 AIRFOIL | Eppler E68 low Reynolds number airfoil Max thickness 13.1% at 32% chord Max camber 3.3% at 50.9% chord | Remove Airfoil details Airfoil plotter |
(e855-il) EPPLER 855 AIRFOIL | Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord Max camber 3.7% at 50.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e853-il,e67-il,e68-il,e855-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e853-il | 50,000 | 9 | 35.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 50,000 | 5 | 35.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 100,000 | 9 | 60.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 100,000 | 5 | 59.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 200,000 | 9 | 85.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 200,000 | 5 | 82.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 500,000 | 9 | 120.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 500,000 | 5 | 103 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 9 | 135.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e853-il | 1,000,000 | 5 | 114.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 50,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 100,000 | 9 | 60.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 100,000 | 5 | 60.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 200,000 | 9 | 86.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 200,000 | 5 | 82.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 500,000 | 9 | 121.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 500,000 | 5 | 107.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 9 | 144.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 5 | 117.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 50,000 | 9 | 33.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 50,000 | 5 | 32.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 100,000 | 9 | 56.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 100,000 | 5 | 56.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 200,000 | 9 | 82.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 200,000 | 5 | 78.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 500,000 | 9 | 114.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 500,000 | 5 | 102.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e68-il | 1,000,000 | 9 | 136.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e68-il | 1,000,000 | 5 | 114.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 50,000 | 9 | 5.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 50,000 | 5 | 23 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 100,000 | 9 | 47 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 100,000 | 5 | 52.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 200,000 | 9 | 76.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 200,000 | 5 | 77.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 500,000 | 9 | 112 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 500,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 9 | 140.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 5 | 122.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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