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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(e1212-il) EPPLER E1212 AIRFOIL | Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord | Remove Airfoil details Airfoil plotter |
(e552-il) EPPLER 552 AIRFOIL | Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1212-il,e552-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1212-il | 50,000 | 9 | 7.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 50,000 | 5 | 23.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 9 | 32.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 9 | 55.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 5 | 59.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 9 | 84.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 5 | 85.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 9 | 109.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 5 | 107.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 50,000 | 9 | 11 at α=-3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 50,000 | 5 | 13.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 100,000 | 9 | 31.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 100,000 | 5 | 43.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 200,000 | 9 | 70.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 200,000 | 5 | 70.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 500,000 | 9 | 106.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 500,000 | 5 | 100.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e552-il | 1,000,000 | 9 | 131 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e552-il | 1,000,000 | 5 | 119.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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