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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(naca652415a05-il) NACA 65(2)-415 a=0.5 | NACA 65(2)-415 a=0.5 airfoil Max thickness 15% at 39.9% chord Max camber 3% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca652415a05-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca652415a05-il | 50,000 | 9 | 20.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 50,000 | 5 | 18.9 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 100,000 | 9 | 33.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 100,000 | 5 | 37 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 200,000 | 9 | 74.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 200,000 | 5 | 73.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 500,000 | 9 | 113.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 500,000 | 5 | 100.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652415a05-il | 1,000,000 | 9 | 134.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652415a05-il | 1,000,000 | 5 | 121.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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