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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(e376-il) EPPLER 376 AIRFOIL | Eppler E376 ultralight airfoil Max thickness 2.5% at 4.3% chord Max camber 9% at 32.7% chord | Remove Airfoil details Airfoil plotter |
(e61-il) E61 (5.64%) | Eppler E61 low Reynolds number airfoil Max thickness 5.7% at 23.8% chord Max camber 6.4% at 51% chord | Remove Airfoil details Airfoil plotter |
(e63-il) E63 (4.25%) | Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord Max camber 5.3% at 50.5% chord | Remove Airfoil details Airfoil plotter |
(e71-il) E71 (5.15%) | Eppler E71 low Reynolds number airfoil Max thickness 5.2% at 25.7% chord Max camber 4.4% at 54% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e376-il,e61-il,e63-il,e71-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e376-il | 50,000 | 9 | 19.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e376-il | 50,000 | 5 | 38.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e376-il | 100,000 | 9 | 105.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e376-il | 100,000 | 5 | 67.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e376-il | 200,000 | 9 | 92.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e376-il | 200,000 | 5 | 95 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e376-il | 500,000 | 9 | 135 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e376-il | 500,000 | 5 | 129.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e376-il | 1,000,000 | 9 | 156.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e376-il | 1,000,000 | 5 | 141.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 50,000 | 9 | 46.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 50,000 | 5 | 45.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 100,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 100,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 200,000 | 9 | 112.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 200,000 | 5 | 110.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 500,000 | 9 | 171 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 500,000 | 5 | 157.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 9 | 214.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 5 | 176.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 50,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 50,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 100,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 100,000 | 5 | 77.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 200,000 | 9 | 112.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 200,000 | 5 | 110 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 500,000 | 9 | 176.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 500,000 | 5 | 160 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 9 | 235.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 5 | 157.7 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 50,000 | 9 | 48.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 50,000 | 5 | 49.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 100,000 | 9 | 75.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 100,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 200,000 | 9 | 108.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 200,000 | 5 | 103.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 500,000 | 9 | 162.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 500,000 | 5 | 143.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 9 | 205 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 5 | 139 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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