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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(e171-il) (Dicke 12.28%) | Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e180-il) E180 (8.59%) | Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord | Remove Airfoil details Airfoil plotter |
(e1230-il) EPPLER 1230 AIRFOIL | Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e171-il,e180-il,e1230-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e171-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 50,000 | 5 | 29.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 100,000 | 9 | 43.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 100,000 | 5 | 41.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 200,000 | 9 | 56.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 200,000 | 5 | 47.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 500,000 | 9 | 65.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 9 | 68.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 50,000 | 9 | 35.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 50,000 | 5 | 36.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 100,000 | 9 | 52.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 100,000 | 5 | 51.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 200,000 | 9 | 71 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 200,000 | 5 | 66 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 500,000 | 9 | 93.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 500,000 | 5 | 82.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 1,000,000 | 9 | 109.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 1,000,000 | 5 | 91.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 9 | 16.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 5 | 24.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 9 | 35.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 9 | 56.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 5 | 60.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 9 | 85.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 5 | 86.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 9 | 111.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 5 | 104.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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