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 |
(fx05191-il) WORTMANN FX 05-191 AIRFOIL | Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord Max camber 2.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(m15-il) NACA M15 AIRFOIL | NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% 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 (falcon-il,fx05191-il,m15-il,fg4-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 | |
| fx05191-il | 50,000 | 9 | 18.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 50,000 | 5 | 14 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 100,000 | 5 | 29.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 9 | 55.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 200,000 | 5 | 57.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 9 | 89.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 9 | 118.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05191-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 50,000 | 9 | 23.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 50,000 | 5 | 30 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 100,000 | 5 | 53.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 200,000 | 9 | 72.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 200,000 | 5 | 72.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 500,000 | 9 | 101.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 500,000 | 5 | 98.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 9 | 124.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 5 | 118.5 at α=6.25° | 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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