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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(goe155-il) GOE 155 (SSW D.1) AIRFOIL | Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord Max camber 5.3% at 39.9% 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 |
(goe226-il) GOE 226 (MVA H.36) AIRFOIL | Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL | Gottingen 198 (L.F.G. 5294) airfoil Max thickness 7.8% at 19.9% chord Max camber 6.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe155-il,goe346-il,goe226-il,goe198-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe155-il | 50,000 | 9 | 40.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 9 | 59.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 9 | 82.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 5 | 78.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 9 | 107.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 5 | 98.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 5 | 111 at α=5.25° | 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 | |
| goe226-il | 50,000 | 9 | 8.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 50,000 | 5 | 28.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 100,000 | 9 | 52.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 100,000 | 5 | 59.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 200,000 | 9 | 85.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 200,000 | 5 | 78.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 500,000 | 9 | 109.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 500,000 | 5 | 102.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 1,000,000 | 9 | 135.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 1,000,000 | 5 | 125.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 50,000 | 9 | 36.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 50,000 | 5 | 43.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 100,000 | 9 | 64.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 100,000 | 5 | 64 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 200,000 | 9 | 88.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 200,000 | 5 | 80.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 500,000 | 9 | 112.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 500,000 | 5 | 92.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe198-il | 1,000,000 | 9 | 117 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe198-il | 1,000,000 | 5 | 92.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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