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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(goe217-il) GOE 217 (MVA MK.12) AIRFOIL | Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord | Remove Airfoil details Airfoil plotter |
(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 |
(goe575-il) GOE 575 AIRFOIL | Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe217-il,goe370-il,goe575-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe217-il | 50,000 | 9 | 5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 50,000 | 5 | 21.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 9 | 40.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 9 | 67 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 9 | 101.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 5 | 99.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 9 | 127.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 5 | 119.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| goe575-il | 50,000 | 9 | 31.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 5 | 32.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 9 | 47.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 5 | 44.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 9 | 57.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 9 | 74.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 5 | 70.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 9 | 88.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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