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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(fg3-il) Fage & Collins 3 | Fage & Collins 3 airfoil Max thickness 10.1% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fg3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fg3-il | 50,000 | 9 | 32.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 50,000 | 5 | 35.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 9 | 48.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 100,000 | 5 | 49.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 9 | 65.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 200,000 | 5 | 65.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 9 | 90.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 500,000 | 5 | 89 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 9 | 111.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg3-il | 1,000,000 | 5 | 108.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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