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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(m18-il) NACA M18 AIRFOIL | NACA/Munk M-18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m18-il | 50,000 | 9 | 11.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 50,000 | 5 | 25.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 100,000 | 9 | 47.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 100,000 | 5 | 50.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 200,000 | 9 | 71.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 200,000 | 5 | 72.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 500,000 | 9 | 103.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 500,000 | 5 | 100.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m18-il | 1,000,000 | 9 | 127.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m18-il | 1,000,000 | 5 | 116.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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