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NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)

NASA/LANGLEY LS(1)-0013 AIRFOIL - NASA/Langley LS(1)-0013 general aviation airfoil


Airfoil ls013-il
Details Dat file Parser  
(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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Lednicer format dat file
Selig format dat file

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Polars for NASA/LANGLEY LS(1)-0013 AIRFOIL (ls013-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ls013-il50,000926.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ls013-il50,000525.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ls013-il100,000936.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ls013-il100,000530.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ls013-il200,000939.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ls013-il200,000539.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ls013-il500,000952.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   ls013-il500,000557.2 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ls013-il1,000,000969.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ls013-il1,000,000571.7 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
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