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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(goe301-il) GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL | Gottingen 301 (Friedrichshafen G 13) airfoil Max thickness 10% at 28.9% chord Max camber 6.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe301-il,fx73cl2152-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe301-il | 50,000 | 9 | 19 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 50,000 | 5 | 38.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 100,000 | 9 | 55.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 100,000 | 5 | 61.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 200,000 | 9 | 81.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 200,000 | 5 | 81.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 500,000 | 9 | 112.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 500,000 | 5 | 108.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe301-il | 1,000,000 | 9 | 138.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe301-il | 1,000,000 | 5 | 128.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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