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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(naca643618-il) NACA 64(3)-618 | NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca643618-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca643618-il | 50,000 | 9 | 18.6 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 50,000 | 5 | 14.9 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 9 | 31.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 100,000 | 5 | 41.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 9 | 74.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 200,000 | 5 | 73.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 9 | 109.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 500,000 | 5 | 103.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 9 | 136.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca643618-il | 1,000,000 | 5 | 124.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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