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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(n14-il) N-14 | N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n14-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n14-il | 50,000 | 9 | 29.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 50,000 | 5 | 27.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 100,000 | 9 | 40.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 100,000 | 5 | 36.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 200,000 | 9 | 48.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 200,000 | 5 | 44.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 500,000 | 9 | 56.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 500,000 | 5 | 58.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 1,000,000 | 9 | 71.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 1,000,000 | 5 | 73.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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