NLF(1)-0115 (nlf0115-il)
NLF(1)-0115 - NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil
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(nlf0115-il) NLF(1)-0115 NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil Max thickness 15% at 44.1% chord. Max camber 1.8% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NLF(1)-0115 1.00000 0.00000 0.99614 0.00060 0.98507 0.00282 0.96792 0.00704 0.94579 0.01293 0.91933 0.01975 0.88867 0.02685 0.85376 0.03411 0.81494 0.04170 0.77287 0.04961 0.72820 0.05769 0.68161 0.06575 0.63378 0.07350 0.58540 0.08060 0.53711 0.08650 0.48908 0.09046 0.44103 0.09238 0.39307 0.09269 0.34578 0.09170 0.29969 0.08957 0.25536 0.08643 0.21335 0.08239 0.17420 0.07751 0.13842 0.07180 0.10644 0.06522 0.07855 0.05773 0.05494 0.04928 0.03560 0.03993 0.02048 0.02992 0.00954 0.01957 0.00270 0.00940 0.00000 0.00012 0.00252 -0.00715 0.01126 -0.01302 0.02600 -0.01859 0.04634 -0.02384 0.07192 -0.02889 0.10230 -0.03376 0.13698 -0.03841 0.17547 -0.04279 0.21723 -0.04681 0.26171 -0.05036 0.30835 -0.05333 0.35657 -0.05558 0.40578 -0.05698 0.45539 -0.05733 0.50482 -0.05642 0.55345 -0.05373 0.60155 -0.04844 0.65013 -0.04101 0.69911 -0.03297 0.74738 -0.02532 0.79388 -0.01850 0.83761 -0.01278 0.87762 -0.00828 0.91305 -0.00497 0.94313 -0.00274 0.96722 -0.00133 0.98498 -0.00042 0.99613 -0.00004 1.00000 0.00000 |
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Polars for NLF(1)-0115 (nlf0115-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlf0115-il | 50,000 | 9 | 30.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0115-il | 50,000 | 5 | 26.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0115-il | 100,000 | 9 | 45.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0115-il | 100,000 | 5 | 41.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0115-il | 200,000 | 9 | 60.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0115-il | 200,000 | 5 | 56 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0115-il | 500,000 | 9 | 81.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0115-il | 500,000 | 5 | 69.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0115-il | 1,000,000 | 9 | 94.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0115-il | 1,000,000 | 5 | 76.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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