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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(e341-il) EPPLER 341 AIRFOIL | Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord | Remove Airfoil details Airfoil plotter |
(e543-il) EPPLER 543 AIRFOIL | Eppler E543 general aviation airfoil Max thickness 17.2% at 40.7% chord Max camber 1.9% at 31% chord | Remove Airfoil details Airfoil plotter |
(e545-il) EPPLER 545 AIRFOIL | Eppler E545 general aviation airfoil Max thickness 17.4% at 39.3% chord Max camber 1.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e341-il,e543-il,e545-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e341-il | 50,000 | 9 | 13.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 50,000 | 5 | 23.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 100,000 | 9 | 28.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 100,000 | 5 | 42.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 200,000 | 9 | 59.1 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 200,000 | 5 | 60.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 500,000 | 9 | 85.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 500,000 | 5 | 80.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 1,000,000 | 9 | 102.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 1,000,000 | 5 | 101.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 50,000 | 9 | 21.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 50,000 | 5 | 17.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 100,000 | 9 | 42.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 100,000 | 5 | 35.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 200,000 | 5 | 58.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 500,000 | 9 | 86.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 500,000 | 5 | 82.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e543-il | 1,000,000 | 9 | 108.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e543-il | 1,000,000 | 5 | 98.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e545-il | 50,000 | 9 | 6.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e545-il | 50,000 | 5 | 19.2 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e545-il | 100,000 | 9 | 43.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e545-il | 100,000 | 5 | 42.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e545-il | 200,000 | 9 | 64.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e545-il | 200,000 | 5 | 63.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e545-il | 500,000 | 9 | 91 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e545-il | 500,000 | 5 | 81.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e545-il | 1,000,000 | 9 | 106.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e545-il | 1,000,000 | 5 | 85 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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