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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(goe286-il) GOE 286 AIRFOIL | Gottingen 286 airfoil Max thickness 9.4% at 29.9% chord Max camber 4.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe276-il) GOE 276 (DAIMLER VII) AIRFOIL | Gottingen 276 (DAIMLER VII) airfoil Max thickness 7.3% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL | Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe286-il,goe276-il,goe173-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe286-il | 50,000 | 9 | 27.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 50,000 | 5 | 37.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 9 | 52.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 100,000 | 5 | 54.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 9 | 72.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 200,000 | 5 | 65.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 9 | 83.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 500,000 | 5 | 78.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 9 | 95.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe286-il | 1,000,000 | 5 | 89.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe276-il | 50,000 | 9 | 36.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe276-il | 50,000 | 5 | 40.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe276-il | 100,000 | 9 | 53 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe276-il | 100,000 | 5 | 56.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe276-il | 200,000 | 9 | 72.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe276-il | 200,000 | 5 | 73.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe276-il | 500,000 | 9 | 97.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe276-il | 500,000 | 5 | 93.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe276-il | 1,000,000 | 9 | 114.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe276-il | 1,000,000 | 5 | 107.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 9 | 33.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 5 | 42.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 9 | 56.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 5 | 60.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 9 | 77.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 5 | 75.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 9 | 101.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 5 | 101.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 9 | 124.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 5 | 122.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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