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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(e485-il) EPPLER 485 AIRFOIL | Eppler E485 tailplane airfoil Max thickness 12.5% at 31.8% chord Max camber 1.1% at 27.1% chord | Remove Airfoil details Airfoil plotter |
(e197-il) E197 (13.49%) | Eppler E197 low Reynolds number airfoil Max thickness 13.5% at 34.6% chord Max camber 2.8% at 43.7% chord | Remove Airfoil details Airfoil plotter |
(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 |
(e228-il) E10(08%) | Eppler E228 low Reynolds number airfoil Max thickness 10.1% at 31.9% chord Max camber 0.3% at 31.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e485-il,e197-il,e171-il,e228-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e485-il | 50,000 | 9 | 27.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 50,000 | 5 | 30.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 100,000 | 9 | 44.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 100,000 | 5 | 44.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 200,000 | 9 | 59.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 200,000 | 5 | 55.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 500,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 500,000 | 5 | 69 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 1,000,000 | 9 | 86.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 1,000,000 | 5 | 81.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e197-il | 50,000 | 9 | 29 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e197-il | 50,000 | 5 | 25.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e197-il | 100,000 | 9 | 52.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e197-il | 100,000 | 5 | 53.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e197-il | 200,000 | 9 | 77.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e197-il | 200,000 | 5 | 75.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e197-il | 500,000 | 9 | 110.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e197-il | 500,000 | 5 | 103.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e197-il | 1,000,000 | 9 | 135.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e197-il | 1,000,000 | 5 | 119.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| e228-il | 50,000 | 9 | 27 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 50,000 | 5 | 28.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 100,000 | 9 | 39.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 100,000 | 5 | 38.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 200,000 | 9 | 51.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 200,000 | 5 | 48.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 500,000 | 9 | 66.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 500,000 | 5 | 61.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e228-il | 1,000,000 | 9 | 75.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e228-il | 1,000,000 | 5 | 71.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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