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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(goe147-il) GOE 147 (MVA H.6) AIRFOIL | Gottingen 147 (MVA H.6) airfoil Max thickness 7.5% at 14.9% chord Max camber 3.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL | Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord Max camber 5.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe346-il) GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL | Gottingen 346 (Friedrichshafen-Staaken) airfoil Max thickness 5.7% at 39.9% chord Max camber 3.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe147-il,goe199-il,goe346-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe147-il | 50,000 | 9 | 29.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 50,000 | 5 | 36.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 100,000 | 9 | 48.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 100,000 | 5 | 49.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 200,000 | 9 | 64.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 200,000 | 5 | 66.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 500,000 | 9 | 86.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 500,000 | 5 | 86.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe147-il | 1,000,000 | 9 | 102.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe147-il | 1,000,000 | 5 | 101.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 50,000 | 5 | 40.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 9 | 55.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 5 | 54.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 9 | 72 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 5 | 67.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 9 | 89.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 5 | 89.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 9 | 108.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 5 | 106.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe346-il | 50,000 | 9 | 40.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe346-il | 50,000 | 5 | 42.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe346-il | 100,000 | 9 | 61.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe346-il | 100,000 | 5 | 59.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe346-il | 200,000 | 9 | 81.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe346-il | 200,000 | 5 | 72.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe346-il | 500,000 | 9 | 95.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe346-il | 500,000 | 5 | 83 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe346-il | 1,000,000 | 9 | 100.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe346-il | 1,000,000 | 5 | 91.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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