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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(e551-il) EPPLER 551 AIRFOIL | Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord Max camber 2.8% at 57.1% chord | Remove Airfoil details Airfoil plotter |
(e637-il) EPPLER 637 AIRFOIL | Eppler E637 airfoil Max thickness 12.1% at 27.6% chord Max camber 3.6% at 23.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e551-il,e637-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e551-il | 50,000 | 9 | 4.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 50,000 | 5 | 14.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 100,000 | 9 | 43.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 100,000 | 5 | 47.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 200,000 | 9 | 72.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 200,000 | 5 | 70 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 500,000 | 9 | 102.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 500,000 | 5 | 95.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 9 | 125.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 5 | 113.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e637-il | 50,000 | 9 | 14.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e637-il | 50,000 | 5 | 24.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e637-il | 100,000 | 9 | 31.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e637-il | 100,000 | 5 | 44.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e637-il | 200,000 | 9 | 62.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e637-il | 200,000 | 5 | 67.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e637-il | 500,000 | 9 | 98 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e637-il | 500,000 | 5 | 98.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e637-il | 1,000,000 | 9 | 126.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e637-il | 1,000,000 | 5 | 117.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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