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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(e230-il) E230 (9.96%) | Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e336-il) EPPLER 336 AIRFOIL | Eppler E336 flying wing airfoil Max thickness 12.8% at 28.1% chord Max camber 2.8% at 23.4% 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 (e230-il,e336-il,e266-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e230-il | 50,000 | 9 | 23 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 50,000 | 5 | 24.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 100,000 | 9 | 32.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 100,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 200,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 200,000 | 5 | 38.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 500,000 | 9 | 50.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 500,000 | 5 | 49.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e230-il | 1,000,000 | 5 | 58 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 50,000 | 9 | 16.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 50,000 | 5 | 25.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 100,000 | 9 | 35.7 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 100,000 | 5 | 44.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 200,000 | 9 | 61.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 200,000 | 5 | 62.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 500,000 | 9 | 87.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 500,000 | 5 | 78.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 9 | 99 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 5 | 96.7 at α=8.75° | 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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