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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(fg2-il) Fage & Collins 2 | Fage & Collins 2 airfoil Max thickness 8.2% at 30% chord Max camber 3.3% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fg2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fg2-il | 50,000 | 9 | 33.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg2-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg2-il | 100,000 | 9 | 51.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg2-il | 100,000 | 5 | 53.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg2-il | 200,000 | 9 | 69.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg2-il | 200,000 | 5 | 69.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg2-il | 500,000 | 9 | 93.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg2-il | 500,000 | 5 | 90.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg2-il | 1,000,000 | 9 | 111.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg2-il | 1,000,000 | 5 | 105.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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