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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(m10-il) NACA M10 AIRFOIL | NACA/Munk M-10 airfoil Max thickness 6.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m10-il | 50,000 | 9 | 34.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 50,000 | 5 | 34.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 100,000 | 9 | 46.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 100,000 | 5 | 45.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 200,000 | 9 | 58.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 200,000 | 5 | 54.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 500,000 | 9 | 72.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 500,000 | 5 | 64.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 9 | 80.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m10-il | 1,000,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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