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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(n2415-il) NACA 2415 | NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n2415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2415-il | 50,000 | 9 | 26.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 50,000 | 5 | 31.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 9 | 46.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 9 | 64.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 9 | 87.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 5 | 79.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 9 | 103 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 5 | 89.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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