NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)
NASA/LANGLEY LS(1)-0013 AIRFOIL - NASA/Langley LS(1)-0013 general aviation airfoil
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(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY LS(1)-0013 AIRFOIL 29. 29. 0.00000 0.00000 0.00624 0.01344 0.01255 0.01892 0.01771 0.02222 0.02470 0.02583 0.03737 0.03075 0.04998 0.03465 0.06260 0.03790 0.07535 0.04075 0.10014 0.04541 0.15007 0.05245 0.19992 0.05750 0.25029 0.06094 0.30055 0.06307 0.34984 0.06407 0.40004 0.06432 0.45013 0.06374 0.50025 0.06203 0.55021 0.05896 0.60038 0.05446 0.65028 0.04868 0.70010 0.04183 0.75018 0.03429 0.80021 0.02638 0.85035 0.01859 0.90019 0.01172 0.95029 0.00633 0.98960 0.00371 1.00000 0.00302 0.00000 0.00000 0.00624 -.01344 0.01255 -.01892 0.01771 -.02222 0.02470 -.02583 0.03737 -.03075 0.04998 -.03465 0.06260 -.03790 0.07535 -.04075 0.10014 -.04541 0.15007 -.05245 0.19992 -.05750 0.25029 -.06094 0.30055 -.06307 0.34984 -.06407 0.40004 -.06432 0.45013 -.06374 0.50025 -.06203 0.55021 -.05896 0.60038 -.05446 0.65028 -.04868 0.70010 -.04183 0.75018 -.03429 0.80021 -.02638 0.85035 -.01859 0.90019 -.01172 0.95029 -.00633 0.98960 -.00371 1.00000 -.00302 |
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Polars for NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls013-il | 50,000 | 9 | 26.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 50,000 | 5 | 25.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 100,000 | 9 | 36.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 100,000 | 5 | 30.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 200,000 | 9 | 39.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 200,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 500,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 500,000 | 5 | 57.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 1,000,000 | 9 | 69.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 1,000,000 | 5 | 71.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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