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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(goe13k-il) GOE 13K AIRFOIL | Gottingen 13K airfoil Max thickness 14.8% at 50% chord Max camber 5.5% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe13k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe13k-il | 50,000 | 9 | 25.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 50,000 | 5 | 20.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 9 | 34.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 100,000 | 5 | 30.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 9 | 45.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 200,000 | 5 | 42.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 500,000 | 5 | 85.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 9 | 129 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe13k-il | 1,000,000 | 5 | 93.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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