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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(goe499-il) GOE 499 AIRFOIL | Gottingen 499 airfoil Max thickness 6.8% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe499-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe499-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 50,000 | 5 | 44.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 9 | 71.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 5 | 69.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 9 | 102.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 5 | 99.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 9 | 149.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 5 | 118.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 9 | 157.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 5 | 111.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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