NACA 2415 (n2415-il)
NACA 2415 - NACA 2415 airfoil
| Details | Dat file | Parser | |
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(n2415-il) NACA 2415 NACA 2415 airfoil Max thickness 15% 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 2415 1.00000 0.00157 0.99740 0.00223 0.98930 0.00419 0.97590 0.00739 0.95733 0.01172 0.93377 0.01705 0.90548 0.02323 0.87275 0.03006 0.83591 0.03738 0.79536 0.04498 0.75154 0.05267 0.70490 0.06025 0.65595 0.06753 0.60524 0.07431 0.55331 0.08040 0.50074 0.08562 0.44811 0.08978 0.39597 0.09272 0.34448 0.09409 0.29469 0.09366 0.24722 0.09140 0.20261 0.08736 0.16142 0.08163 0.12411 0.07438 0.09112 0.06580 0.06282 0.05615 0.03952 0.04566 0.02145 0.03460 0.00878 0.02319 0.00161 0.01161 0.00000 0.00000 0.00387 -0.01106 0.01308 -0.02103 0.02750 -0.02985 0.04694 -0.03748 0.07115 -0.04387 0.09986 -0.04899 0.13275 -0.05282 0.16945 -0.05539 0.20960 -0.05676 0.25278 -0.05703 0.29857 -0.05633 0.34651 -0.05483 0.39612 -0.05272 0.44737 -0.05003 0.49926 -0.04673 0.55122 -0.04298 0.60267 -0.03893 0.65306 -0.03472 0.70184 -0.03048 0.74846 -0.02628 0.79242 -0.02222 0.83322 -0.01836 0.87040 -0.01477 0.90354 -0.01151 0.93225 -0.00862 0.95622 -0.00616 0.97516 -0.00419 0.98885 -0.00275 0.99712 -0.00187 1.00000 -0.00157 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 2415 (n2415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2415-il | 50,000 | 9 | 26.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 50,000 | 5 | 31.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 9 | 46.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 9 | 64.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 9 | 87.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 5 | 79.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 9 | 103 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 5 | 89.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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