NASA NLF1015 (nlf1015-il)
NASA NLF1015 - NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil
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(nlf1015-il) NASA NLF1015 NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord. Max camber 4.3% at 62.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NASA NLF1015 1.00000 0.00000 0.99657 0.00146 0.98712 0.00583 0.97298 0.01248 0.95446 0.02023 0.93125 0.02865 0.90350 0.03788 0.87177 0.04788 0.83659 0.05840 0.79853 0.06915 0.75812 0.07981 0.71589 0.09000 0.67236 0.09933 0.62799 0.10732 0.58299 0.11337 0.53726 0.11727 0.49085 0.11922 0.44416 0.11947 0.39771 0.11815 0.35196 0.11535 0.30741 0.11115 0.26449 0.10564 0.22364 0.09892 0.18527 0.09110 0.14974 0.08232 0.11740 0.07273 0.08855 0.06249 0.06343 0.05179 0.04226 0.04085 0.02521 0.02995 0.01241 0.01938 0.00398 0.00957 0.00008 0.00117 0.00208 -0.00535 0.01053 -0.01088 0.02456 -0.01608 0.04389 -0.02071 0.06828 -0.02466 0.09749 -0.02791 0.13119 -0.03046 0.16903 -0.03230 0.21056 -0.03346 0.25529 -0.03397 0.30270 -0.03384 0.35221 -0.03306 0.40319 -0.03160 0.45501 -0.02941 0.50699 -0.02620 0.55895 -0.02150 0.61119 -0.01549 0.66352 -0.00895 0.71529 -0.00256 0.76576 0.00311 0.81405 0.00755 0.85913 0.01035 0.89987 0.01127 0.93510 0.01032 0.96363 0.00772 0.98422 0.00416 0.99617 0.00114 1.00000 0.00000 |
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Polars for NASA NLF1015 (nlf1015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf1015-il | 50,000 | 9 | 25.8 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 50,000 | 5 | 21.9 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 9 | 40.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 5 | 38.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 9 | 75.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 5 | 77.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 9 | 130.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 5 | 125.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 9 | 167.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 5 | 154.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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