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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(naca1408-il) NACA 1408 | NACA 1408 airfoil Max thickness 8% at 30% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca1408-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca1408-il | 50,000 | 9 | 32.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 50,000 | 5 | 31.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 100,000 | 9 | 44.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 100,000 | 5 | 40.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 200,000 | 9 | 54.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 200,000 | 5 | 47.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 500,000 | 9 | 66.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 500,000 | 5 | 62.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 1,000,000 | 9 | 72.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 1,000,000 | 5 | 77.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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