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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(naca642415-il) NACA 64(2)-415 | NACA 64(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca642415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca642415-il | 50,000 | 9 | 27.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642415-il | 50,000 | 5 | 25.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642415-il | 100,000 | 9 | 51.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642415-il | 100,000 | 5 | 51.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642415-il | 200,000 | 9 | 75.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642415-il | 200,000 | 5 | 70 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642415-il | 500,000 | 9 | 101.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642415-il | 500,000 | 5 | 90.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642415-il | 1,000,000 | 9 | 120.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642415-il | 1,000,000 | 5 | 103.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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