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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(e540-il) EPPLER 540 AIRFOIL | Eppler E540 general aviation airfoil Max thickness 16.9% at 45.5% chord Max camber 1.6% at 35.7% chord | Remove Airfoil details Airfoil plotter |
(goe366-il) GOE 366 AIRFOIL | Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(stf86361-il) EPPLER STF 863-615 AIRFOIL | Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord Max camber 4.2% at 72.3% chord | Remove Airfoil details Airfoil plotter |
(goe122-il) GOE 122 (MVA H.2) AIRFOIL | Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e540-il,goe366-il,stf86361-il,goe122-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e540-il | 50,000 | 9 | 24.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e540-il | 50,000 | 5 | 20.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e540-il | 100,000 | 9 | 38.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e540-il | 100,000 | 5 | 33.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e540-il | 200,000 | 9 | 54 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e540-il | 200,000 | 5 | 57 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e540-il | 500,000 | 9 | 85.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e540-il | 500,000 | 5 | 82.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e540-il | 1,000,000 | 9 | 110 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e540-il | 1,000,000 | 5 | 97.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 50,000 | 9 | 8.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 50,000 | 5 | 30.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 100,000 | 9 | 51.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 100,000 | 5 | 55 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 200,000 | 9 | 82.6 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 200,000 | 5 | 73.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 500,000 | 9 | 102.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 500,000 | 5 | 97.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe366-il | 1,000,000 | 9 | 128.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe366-il | 1,000,000 | 5 | 121.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 50,000 | 9 | 22.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 50,000 | 5 | 23.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 100,000 | 9 | 32.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 100,000 | 5 | 34.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 200,000 | 9 | 54.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 200,000 | 5 | 56.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 500,000 | 9 | 92.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 500,000 | 5 | 98.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stf86361-il | 1,000,000 | 9 | 145.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stf86361-il | 1,000,000 | 5 | 142.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 50,000 | 9 | 37.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 50,000 | 5 | 39.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 9 | 55.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 100,000 | 5 | 56.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 9 | 73.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 200,000 | 5 | 72.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 9 | 95.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 500,000 | 5 | 89.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 9 | 110.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe122-il | 1,000,000 | 5 | 97.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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