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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(goe365-il) GOE 365 AIRFOIL | Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe242-il) GOE 242 (MVA PR.2) AIRFOIL | Gottingen 242 (MVA PR.2) airfoil Max thickness 16.2% at 29.6% chord Max camber 7.5% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe365-il,goe242-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe365-il | 50,000 | 9 | 27.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 50,000 | 5 | 34.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 100,000 | 9 | 55.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 100,000 | 5 | 55.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 200,000 | 9 | 79.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 200,000 | 5 | 73.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 500,000 | 9 | 107.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 500,000 | 5 | 90.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe365-il | 1,000,000 | 9 | 120.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe365-il | 1,000,000 | 5 | 99.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 50,000 | 9 | 6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 50,000 | 5 | 20.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 100,000 | 9 | 46.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 100,000 | 5 | 54.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 200,000 | 5 | 80.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 500,000 | 9 | 116.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 500,000 | 5 | 114.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe242-il | 1,000,000 | 9 | 146.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe242-il | 1,000,000 | 5 | 137.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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