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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(goe14-il) GOE 14 AIRFOIL | Gottingen 14 airfoil Max thickness 9.9% at 29.8% chord Max camber 6.9% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe14-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe14-il | 50,000 | 9 | 17.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14-il | 50,000 | 5 | 34.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14-il | 100,000 | 9 | 46.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14-il | 100,000 | 5 | 53.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14-il | 200,000 | 9 | 70.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14-il | 200,000 | 5 | 70 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14-il | 500,000 | 9 | 98.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14-il | 500,000 | 5 | 93.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe14-il | 1,000,000 | 9 | 122.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe14-il | 1,000,000 | 5 | 111.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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