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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(e403-il) EPPLER 403 AIRFOIL | Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord | Remove Airfoil details Airfoil plotter |
(e421-il) EPPLER 421 AIRFOIL | Eppler E421 high lift airfoil Max thickness 14.5% at 26% chord Max camber 8.6% at 37.4% chord | Remove Airfoil details Airfoil plotter |
(e417-il) EPPLER 417 AIRFOIL | Eppler E417 general purpose airfoil Max thickness 14.2% at 38.3% chord Max camber 3.1% at 76.3% chord | Remove Airfoil details Airfoil plotter |
(e475-il) E475 (15.01%) | Eppler E475 aerobatic aircraft airfoil Max thickness 15% at 21.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e403-il,e421-il,e417-il,e475-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e403-il | 50,000 | 9 | 33.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 50,000 | 5 | 29.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 100,000 | 9 | 47.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 100,000 | 5 | 45.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 200,000 | 9 | 66.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 200,000 | 5 | 66.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 500,000 | 9 | 106.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 500,000 | 5 | 98.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e403-il | 1,000,000 | 9 | 138.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e403-il | 1,000,000 | 5 | 115.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 50,000 | 5 | 20 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 100,000 | 9 | 27.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 100,000 | 5 | 48 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 200,000 | 9 | 63 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 200,000 | 5 | 74.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 500,000 | 9 | 107.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 500,000 | 5 | 109.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 1,000,000 | 9 | 141.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 1,000,000 | 5 | 141.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 50,000 | 9 | 33.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 50,000 | 5 | 30.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 100,000 | 9 | 46.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 100,000 | 5 | 46 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 200,000 | 9 | 65.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 200,000 | 5 | 66.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 500,000 | 9 | 103.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 500,000 | 5 | 94.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e417-il | 1,000,000 | 9 | 135.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e417-il | 1,000,000 | 5 | 112.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 50,000 | 9 | 20.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 50,000 | 5 | 24.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 100,000 | 9 | 30.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 100,000 | 5 | 36.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 200,000 | 9 | 46.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 200,000 | 5 | 51.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 500,000 | 9 | 72.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 500,000 | 5 | 71 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 9 | 90 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 5 | 83.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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