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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(fx601001-il) FX 60-100 (126) AIRFOIL | Wortmann FX 60-100 (126) airfoil Max thickness 10.1% at 30.8% chord Max camber 3.6% at 59.7% chord | Remove Airfoil details Airfoil plotter |
(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 |
(fx082512-il) WORTMANN FX 082-512 AIRFOIL | Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord | Remove Airfoil details Airfoil plotter |
(fx60126-il) WORTMANN FX 60-126 AIRFOIL | Wortmann FX 60-126 airfoil Max thickness 12.6% at 27.9% chord Max camber 3.6% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(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 (fx601001-il,fg3-il,fx082512-il,fx60126-il,fg4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx601001-il | 50,000 | 9 | 38.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 9 | 61 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 5 | 62.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 9 | 84.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 9 | 103 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 5 | 92.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 9 | 116.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 5 | 101.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| fx082512-il | 50,000 | 9 | 31.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 9 | 46.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 100,000 | 5 | 47.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 9 | 63.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 200,000 | 5 | 60.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 9 | 83.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 500,000 | 5 | 75.3 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 9 | 99.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx082512-il | 1,000,000 | 5 | 82.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 50,000 | 9 | 34.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 50,000 | 5 | 39.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 100,000 | 5 | 58.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 200,000 | 9 | 79.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 200,000 | 5 | 75.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 500,000 | 9 | 104 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 500,000 | 5 | 88.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60126-il | 1,000,000 | 9 | 112.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60126-il | 1,000,000 | 5 | 95.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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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