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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(goe517-il) GOE 517 AIRFOIL | Gottingen 517 airfoil Max thickness 7% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(usa41-il) USA 41 AIRFOIL | USA-41 airfoil Max thickness 6.6% at 30% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe371-il) GOE 371 AIRFOIL | Gottingen 371 airfoil Max thickness 7% at 29.9% chord Max camber 4.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe517-il,usa41-il,goe371-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe517-il | 50,000 | 9 | 37.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 50,000 | 5 | 40.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 9 | 55.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 9 | 75 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 5 | 79.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 9 | 103 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 5 | 102 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 9 | 121.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 5 | 117.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa41-il | 50,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa41-il | 50,000 | 5 | 42.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa41-il | 100,000 | 9 | 59.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa41-il | 100,000 | 5 | 60.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa41-il | 200,000 | 9 | 79.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa41-il | 200,000 | 5 | 79.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa41-il | 500,000 | 9 | 107.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa41-il | 500,000 | 5 | 104.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa41-il | 1,000,000 | 9 | 129.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa41-il | 1,000,000 | 5 | 122.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 50,000 | 5 | 43.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 100,000 | 9 | 61.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 100,000 | 5 | 62.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 200,000 | 9 | 82 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 200,000 | 5 | 80 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 500,000 | 9 | 108.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 500,000 | 5 | 103.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 1,000,000 | 9 | 129.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 1,000,000 | 5 | 120.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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