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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(m19-il) NACA M19 AIRFOIL | NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(m20-il) NACA M20 AIRFOIL | NACA/Munk M-20 airfoil Max thickness 8.2% at 30% chord Max camber 6.1% 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 |
(m17-il) NACA M17 AIRFOIL | NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m19-il,m20-il,m1-il,m17-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m19-il | 50,000 | 9 | 20.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 50,000 | 5 | 37.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 100,000 | 9 | 57.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 100,000 | 5 | 57.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 200,000 | 9 | 77.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 200,000 | 5 | 75.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 500,000 | 9 | 102.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 500,000 | 5 | 83 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 9 | 117.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 50,000 | 9 | 10.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 50,000 | 5 | 26.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 100,000 | 9 | 55.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 100,000 | 5 | 56.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 200,000 | 9 | 78.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 200,000 | 5 | 78 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 500,000 | 9 | 108.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 500,000 | 5 | 105.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 9 | 131.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m20-il | 1,000,000 | 5 | 125.3 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 | |
| m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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