NACA 2414 (n2414-il)
NACA 2414 - NACA 2414 airfoil
| Details | Dat file | Parser | |
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(n2414-il) NACA 2414 NACA 2414 airfoil Max thickness 14% at 29.5% chord. Max camber 2% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2414 1.00000 0.00147 0.99739 0.00210 0.98929 0.00396 0.97587 0.00700 0.95729 0.01112 0.93372 0.01620 0.90542 0.02207 0.87267 0.02857 0.83582 0.03552 0.79527 0.04274 0.75143 0.05004 0.70480 0.05723 0.65586 0.06412 0.60515 0.07053 0.55324 0.07629 0.50069 0.08120 0.44808 0.08512 0.39598 0.08787 0.34454 0.08913 0.29482 0.08866 0.24740 0.08645 0.20285 0.08255 0.16169 0.07707 0.12440 0.07014 0.09141 0.06198 0.06310 0.05281 0.03977 0.04289 0.02165 0.03245 0.00892 0.02171 0.00169 0.01085 0.00000 0.00000 0.00379 -0.01031 0.01293 -0.01956 0.02730 -0.02770 0.04669 -0.03471 0.07087 -0.04054 0.09957 -0.04516 0.13246 -0.04858 0.16918 -0.05082 0.20937 -0.05195 0.25260 -0.05208 0.29844 -0.05133 0.34644 -0.04987 0.39611 -0.04787 0.44739 -0.04537 0.49931 -0.04232 0.55129 -0.03886 0.60276 -0.03516 0.65316 -0.03132 0.70194 -0.02745 0.74857 -0.02365 0.79252 -0.01998 0.83331 -0.01650 0.87048 -0.01328 0.90360 -0.01035 0.93230 -0.00776 0.95626 -0.00557 0.97518 -0.00381 0.98886 -0.00252 0.99713 -0.00173 1.00000 -0.00147 |
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Polars for NACA 2414 (n2414-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2414-il | 50,000 | 9 | 29.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 50,000 | 5 | 32.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 9 | 47.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 5 | 48.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 9 | 65.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 5 | 62.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 5 | 79.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 9 | 103.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 5 | 90 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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