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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(fg4-il) Fage & Collins 4 | Fage & Collins 4 airfoil Max thickness 12.7% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fg4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fg4-il | 50,000 | 9 | 30.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 50,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 9 | 51.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 100,000 | 5 | 47.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 9 | 65.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 200,000 | 5 | 47 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 9 | 62.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 500,000 | 5 | 58.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 9 | 71.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fg4-il | 1,000,000 | 5 | 72.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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