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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(goe301-il) GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL | Gottingen 301 (Friedrichshafen G 13) airfoil Max thickness 10% at 28.9% chord Max camber 6.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe14k-il) GOE 14K AIRFOIL | Gottingen 14K airfoil Max thickness 12% at 50% chord Max camber 2.7% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe114-il) GOE 114 (MVA MK.1) AIRFOIL | Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe301-il,goe14k-il,goe114-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe301-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 50,000 | 5 | 38.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 100,000 | 9 | 55.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 100,000 | 5 | 61.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 200,000 | 9 | 81.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 200,000 | 5 | 81.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 500,000 | 9 | 112.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 500,000 | 5 | 108.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 1,000,000 | 9 | 138.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 1,000,000 | 5 | 128.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14k-il | 50,000 | 9 | 25.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14k-il | 50,000 | 5 | 25.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14k-il | 100,000 | 9 | 36 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14k-il | 100,000 | 5 | 38.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14k-il | 200,000 | 9 | 60.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14k-il | 200,000 | 5 | 59.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14k-il | 500,000 | 9 | 100.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14k-il | 500,000 | 5 | 76.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14k-il | 1,000,000 | 9 | 98.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14k-il | 1,000,000 | 5 | 86.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe114-il | 50,000 | 9 | 35.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe114-il | 50,000 | 5 | 32.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe114-il | 100,000 | 9 | 49.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe114-il | 100,000 | 5 | 44.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe114-il | 200,000 | 9 | 60.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe114-il | 200,000 | 5 | 50.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe114-il | 500,000 | 9 | 93.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe114-il | 500,000 | 5 | 74.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe114-il | 1,000,000 | 9 | 70.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe114-il | 1,000,000 | 5 | 67.6 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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