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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(goe415-il) GOE 415 AIRFOIL | Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(naca653618-il) NACA 65(3)-618 | NACA 65(3)-618 airfoil Max thickness 18% at 39.8% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe601-il) GOE 601 AIRFOIL | Gottingen 601 airfoil Max thickness 16% at 39% chord Max camber 2.5% at 49% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe415-il,naca653618-il,goe601-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe415-il | 50,000 | 9 | 34 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 50,000 | 5 | 37.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 100,000 | 9 | 52 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 100,000 | 5 | 53.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 200,000 | 9 | 68.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 200,000 | 5 | 69.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 500,000 | 9 | 92.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 500,000 | 5 | 90.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 1,000,000 | 9 | 109.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 1,000,000 | 5 | 106.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 50,000 | 9 | 17.8 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 50,000 | 5 | 15.3 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 100,000 | 9 | 27.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 100,000 | 5 | 29 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 200,000 | 9 | 67.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 200,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 500,000 | 9 | 110.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 500,000 | 5 | 105.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca653618-il | 1,000,000 | 9 | 138.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca653618-il | 1,000,000 | 5 | 128.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 50,000 | 9 | 25.2 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 50,000 | 5 | 28 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 100,000 | 9 | 47.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 100,000 | 5 | 44.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 200,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 200,000 | 5 | 57.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 500,000 | 9 | 82.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 500,000 | 5 | 69 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe601-il | 1,000,000 | 9 | 91.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe601-il | 1,000,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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