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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(goe503-il) GOE 503 AIRFOIL | Gottingen 503 airfoil Max thickness 15.6% at 29.7% chord Max camber 7% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe503-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe503-il | 50,000 | 9 | 4.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 50,000 | 5 | 15.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 100,000 | 9 | 32.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 100,000 | 5 | 46.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 200,000 | 9 | 68.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 200,000 | 5 | 67 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 500,000 | 9 | 96.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 500,000 | 5 | 91.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe503-il | 1,000,000 | 9 | 120.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe503-il | 1,000,000 | 5 | 109.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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