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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(m14-il) NACA M14 AIRFOIL | NACA/Munk M-14 airfoil Max thickness 8.1% at 30% chord Max camber 3.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(m26-il) NACA M26 AIRFOIL | NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(m1-il) NACA-M1 AIRFOIL | NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(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 |
(fx3-il) WORTMANN FX 3 AIRFOIL | Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m14-il,m26-il,m1-il,fg2-il,fx3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m14-il | 50,000 | 9 | 38.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m14-il | 50,000 | 5 | 38.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m14-il | 100,000 | 9 | 57.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m14-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m14-il | 200,000 | 9 | 76.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m14-il | 200,000 | 5 | 75.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m14-il | 500,000 | 9 | 102.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m14-il | 500,000 | 5 | 98.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m14-il | 1,000,000 | 9 | 121.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m14-il | 1,000,000 | 5 | 113.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 50,000 | 9 | 6.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 50,000 | 5 | 14 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 100,000 | 9 | 16.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 100,000 | 5 | 41.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 200,000 | 9 | 78.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 200,000 | 5 | 78.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 500,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 9 | 141.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 5 | 113.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 50,000 | 9 | 18.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 50,000 | 5 | 20.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 100,000 | 9 | 27.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 100,000 | 5 | 24.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 200,000 | 9 | 32.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 200,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 500,000 | 9 | 38.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 500,000 | 5 | 50.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 9 | 56 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m1-il | 1,000,000 | 5 | 63.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| fx3-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 50,000 | 0 | 18.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 5 | 23.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 0 | 23.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 5 | 32.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 0 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 5 | 44.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 0 | 40.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 5 | 58.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 0 | 54.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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