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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(e433-il) EPPLER 433 AIRFOIL | Eppler E433 sailplane airfoil Max thickness 14.2% at 42.6% chord Max camber 3.9% at 42.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e433-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e433-il | 50,000 | 9 | 29.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e433-il | 50,000 | 5 | 26.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e433-il | 100,000 | 9 | 52.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e433-il | 100,000 | 5 | 49.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e433-il | 200,000 | 9 | 81.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e433-il | 200,000 | 5 | 76.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e433-il | 500,000 | 9 | 116.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e433-il | 500,000 | 5 | 107.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e433-il | 1,000,000 | 9 | 144.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e433-il | 1,000,000 | 5 | 126.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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