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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(goe372-il) GOE 372 AIRFOIL | Gottingen 372 airfoil Max thickness 6.2% at 29.9% chord Max camber 4.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe362-il) GOE 362 AIRFOIL | Gottingen 362 airfoil Max thickness 6.6% at 20% chord Max camber 5.3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe372-il,goe362-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe372-il | 50,000 | 9 | 43.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe372-il | 50,000 | 5 | 42.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe372-il | 100,000 | 9 | 62.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe372-il | 100,000 | 5 | 60.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe372-il | 200,000 | 9 | 82.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe372-il | 200,000 | 5 | 77.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe372-il | 500,000 | 9 | 108.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe372-il | 500,000 | 5 | 93 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe372-il | 1,000,000 | 9 | 126.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe372-il | 1,000,000 | 5 | 89.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 9 | 37.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 50,000 | 5 | 43.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 9 | 58.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 100,000 | 5 | 63.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 9 | 79.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 200,000 | 5 | 81.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 9 | 109.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 500,000 | 5 | 108.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 9 | 131.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe362-il | 1,000,000 | 5 | 127.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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