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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(naca2418-il) NACA 2418 | NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca2418-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2418-il | 50,000 | 9 | 8.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 50,000 | 5 | 27.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 9 | 42.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 100,000 | 5 | 44 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 9 | 60.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 200,000 | 5 | 58.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 9 | 83.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 500,000 | 5 | 75.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 9 | 97.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2418-il | 1,000,000 | 5 | 87.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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