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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(n64015a-il) NACA 642-015A AIRFOIL | NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n64015a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64015a-il | 50,000 | 9 | 28.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015a-il | 50,000 | 5 | 27.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015a-il | 100,000 | 9 | 43.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015a-il | 100,000 | 5 | 36.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015a-il | 200,000 | 9 | 49.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015a-il | 200,000 | 5 | 44.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015a-il | 500,000 | 9 | 64.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015a-il | 500,000 | 5 | 52.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64015a-il | 1,000,000 | 9 | 70.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64015a-il | 1,000,000 | 5 | 65.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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