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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(e399-il) EPPLER 399 AIRFOIL | Eppler E399 human powered aircraft airfoil Max thickness 14.8% at 29% chord Max camber 5.1% at 51.4% chord | Remove Airfoil details Airfoil plotter |
(e546-il) EPPLER 546 AIRFOIL | Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e399-il,e546-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e399-il | 50,000 | 9 | 6.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 50,000 | 5 | 16.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 100,000 | 9 | 46.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 100,000 | 5 | 54 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 200,000 | 9 | 83.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 200,000 | 5 | 85.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 500,000 | 9 | 127.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 500,000 | 5 | 123.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 9 | 161.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e399-il | 1,000,000 | 5 | 142.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 50,000 | 9 | 8.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 50,000 | 5 | 21.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 100,000 | 9 | 44.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 100,000 | 5 | 43.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 200,000 | 9 | 61.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 200,000 | 5 | 61.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 500,000 | 9 | 87.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 500,000 | 5 | 82.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e546-il | 1,000,000 | 9 | 106.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e546-il | 1,000,000 | 5 | 96.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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