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 |
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Polars for (m14-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 | |
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