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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(m11-il) NACA M11 AIRFOIL | NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% 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 |
(m16-il) NACA M16 AIRFOIL | NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(m12-il) NACA M12 AIRFOIL | NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m11-il,fg4-il,m16-il,m12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m11-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 50,000 | 5 | 35.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 100,000 | 9 | 50.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 100,000 | 5 | 48.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 200,000 | 9 | 65.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 200,000 | 5 | 60.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 500,000 | 9 | 84.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 500,000 | 5 | 75.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 9 | 96.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m11-il | 1,000,000 | 5 | 82.5 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 | |
| m16-il | 50,000 | 9 | 39 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 100,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 100,000 | 5 | 53.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 200,000 | 5 | 68.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 500,000 | 9 | 92.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 500,000 | 5 | 88.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 5 | 102.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 50,000 | 9 | 31.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 100,000 | 9 | 49 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 100,000 | 5 | 48.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 200,000 | 5 | 62.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 500,000 | 5 | 77.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 9 | 98.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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