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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(e479-il) EPPLER 479 AIRFOIL | Eppler E479 aerobatic aircraft airfoil Max thickness 16.6% at 25.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e344-il) EPPLER 344 AIRFOIL | Eppler E344 flying wing airfoil Max thickness 14.7% at 29.9% chord Max camber 4.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(e266-il) EPPLER 266 AIRFOIL | Eppler E266 general purpose airfoil Max thickness 17.3% at 39.8% chord Max camber 3.1% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e479-il,e344-il,e266-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e479-il | 50,000 | 9 | 15.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 50,000 | 5 | 23.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 100,000 | 9 | 33.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 100,000 | 5 | 39 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 200,000 | 9 | 52.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 200,000 | 5 | 54.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 500,000 | 9 | 76.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 500,000 | 5 | 74.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 9 | 95.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 5 | 88.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 50,000 | 9 | 14.3 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 50,000 | 5 | 24.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 100,000 | 9 | 31.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 100,000 | 5 | 44 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 200,000 | 9 | 58 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 500,000 | 9 | 94.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 500,000 | 5 | 91.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 9 | 118.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 5 | 116.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 50,000 | 9 | 13.9 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 50,000 | 5 | 13.4 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 100,000 | 9 | 26 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 100,000 | 5 | 23.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 200,000 | 9 | 61.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 200,000 | 5 | 59.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 500,000 | 9 | 100.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 500,000 | 5 | 100 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 9 | 131.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e266-il | 1,000,000 | 5 | 124.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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