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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(n64008a-il) NACA 64-008A AIRFOIL | NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n64008a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64008a-il | 50,000 | 9 | 19.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 5 | 23.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 9 | 32.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 5 | 30.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 9 | 41 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 5 | 35 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 9 | 46.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 5 | 44.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 9 | 49.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 5 | 59.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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