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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(goe310-il) GOE 310 (MVA H.42) AIRFOIL | Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe285-il) GOE 285 AIRFOIL | Gottingen 285 airfoil Max thickness 11.7% at 30% chord Max camber 3.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (goe310-il,goe285-il,goe301-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe310-il | 50,000 | 9 | 37.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 50,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 100,000 | 9 | 59.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 100,000 | 5 | 58.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 200,000 | 9 | 80.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 200,000 | 5 | 73 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 500,000 | 9 | 99.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 500,000 | 5 | 72.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe310-il | 1,000,000 | 9 | 87.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe310-il | 1,000,000 | 5 | 87.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 50,000 | 9 | 26.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 50,000 | 5 | 34.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 9 | 47.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 100,000 | 5 | 50.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 9 | 65.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 200,000 | 5 | 65.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 9 | 89.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 500,000 | 5 | 87 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 9 | 109.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe285-il | 1,000,000 | 5 | 103.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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