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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(goe370-il) GOE 370 AIRFOIL | Gottingen 370 airfoil Max thickness 4.7% at 20% chord Max camber 5.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (goe370-il,goe310-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe370-il | 50,000 | 9 | 45.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 50,000 | 5 | 44.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 100,000 | 9 | 67.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 100,000 | 5 | 67.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 200,000 | 9 | 92 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 200,000 | 5 | 92.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 500,000 | 9 | 128.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 500,000 | 5 | 121.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe370-il | 1,000,000 | 9 | 154.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe370-il | 1,000,000 | 5 | 119.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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