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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(e603-il) EPPLER 603 AIRFOIL | Eppler E603 general purpose airfoil Max thickness 19% at 40% chord Max camber 3.6% at 35.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e603-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e603-il | 50,000 | 9 | 4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 50,000 | 5 | 10.2 at α=15.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 100,000 | 9 | 26.6 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 100,000 | 5 | 22.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 200,000 | 9 | 56.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 200,000 | 5 | 63 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 500,000 | 9 | 103.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 500,000 | 5 | 103.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 1,000,000 | 9 | 136.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 1,000,000 | 5 | 127.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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