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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(naca652415-il) NACA 65(2)-415 | NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca652415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca652415-il | 50,000 | 9 | 23.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415-il | 50,000 | 5 | 24 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415-il | 100,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415-il | 100,000 | 5 | 46.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415-il | 200,000 | 9 | 70.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415-il | 200,000 | 5 | 68 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415-il | 500,000 | 9 | 100.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415-il | 500,000 | 5 | 91.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415-il | 1,000,000 | 9 | 120.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415-il | 1,000,000 | 5 | 105.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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