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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(naca633018-il) NACA 63(3)-018 | NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca633018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca633018-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 5 | 20.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 5 | 61.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 5 | 65.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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