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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(e337-il) EPPLER 337 AIRFOIL | Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord | Remove Airfoil details Airfoil plotter |
(e562-il) EPPLER 562 AIRFOIL | Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord Max camber 4% at 50.8% chord | Remove Airfoil details Airfoil plotter |
(goe362-il) GOE 362 AIRFOIL | Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e337-il,e562-il,goe362-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e337-il | 50,000 | 9 | 16 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 100,000 | 9 | 34.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 100,000 | 5 | 45.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 200,000 | 9 | 62.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 200,000 | 5 | 65.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 500,000 | 9 | 92.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 500,000 | 5 | 84.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 9 | 107.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 5 | 103.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 50,000 | 9 | 11.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 50,000 | 5 | 33.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 100,000 | 9 | 49.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 100,000 | 5 | 55.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 200,000 | 9 | 73.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 500,000 | 9 | 104.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 500,000 | 5 | 100.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 9 | 129.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 5 | 115.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 9 | 37.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 5 | 43.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 9 | 58.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 5 | 63.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 9 | 79.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 5 | 81.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 9 | 109.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 5 | 108.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 9 | 131.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 5 | 127.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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