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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(falcon-il) Falcon | Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane Max thickness 13.7% at 30.6% chord Max camber 1.6% at 20.5% chord | Remove Airfoil details Airfoil plotter |
(fx6617a2-il) FX 66-17AII-182 AIRFOIL | Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx63100-il) FX 63-100 AIRFOIL | Wortmann FX 63-100 airfoil Max thickness 9.9% at 30.8% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (falcon-il,fx6617a2-il,fx73cl2152-il,fx63100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| falcon-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 50,000 | 5 | 30.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 100,000 | 9 | 41.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 100,000 | 5 | 44.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 200,000 | 9 | 58.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 200,000 | 5 | 58.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 500,000 | 9 | 81.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 500,000 | 5 | 78.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| falcon-il | 1,000,000 | 9 | 98.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| falcon-il | 1,000,000 | 5 | 92.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 9 | 4.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 5 | 8.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 9 | 5.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 9 | 65 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 5 | 67.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 9 | 104.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 5 | 102 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 9 | 131.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 5 | 125.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 50,000 | 9 | 43 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 50,000 | 5 | 44.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 100,000 | 9 | 67 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 100,000 | 5 | 67.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 200,000 | 9 | 92.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 200,000 | 5 | 90 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 500,000 | 9 | 121.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 500,000 | 5 | 106.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63100-il | 1,000,000 | 9 | 136.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63100-il | 1,000,000 | 5 | 115.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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