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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(n64215-il) NACA 64-215 AIRFOIL | NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n64215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64215-il | 50,000 | 9 | 28.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 100,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 100,000 | 5 | 44.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 200,000 | 9 | 63.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 200,000 | 5 | 58.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 500,000 | 9 | 85.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 500,000 | 5 | 73.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 1,000,000 | 9 | 99.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 1,000,000 | 5 | 79.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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