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NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)

NASA/LANGLEY NLF(1)-0215F AIRFOIL - NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil


Airfoil nlf0215f-il
Details Dat file Parser  
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL
NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil
Max thickness 15% at 37.7% chord.
Max camber 4% at 42.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/LANGLEY NLF(1)-0215F AIRFOIL
33.        29.
 
 0.00000   0.00000
  .00240    .00917
  .00909    .01947
  .02004    .03027
  .03527    .04120
  .05469    .05201
  .07816    .06250
  .10546    .07247
  .13635    .08175
  .17050    .09019
  .20758    .09761
  .24720    .10389
  .28894    .10887
  .33237    .11240
  .37702    .11428
  .42253    .11427
  .46864    .11219
  .51524    .10784
  .56247    .10147
  .61010    .09373
  .65752    .08513
  .70408    .07603
  .74914    .06673
  .79206    .05746
  .83222    .04844
  .86902    .03983
  .90193    .03175
  .93044    .02428
  .95409    .01737
  .97285    .01082
  .98710    .00507
  .99658    .00126
 1.00000    .00000
 
 0.00000   0.00000
  .00245   -.00704
  .01099   -.01211
  .02592   -.01656
  .04653   -.02052
  .07242   -.02399
  .10324   -.02699
  .13854   -.02954
  .17788   -.03166
  .22073   -.03334
  .26654   -.03456
  .31473   -.03531
  .36468   -.03554
  .41576   -.03519
  .46731   -.03415
  .51867   -.03225
  .56920   -.02925
  .61825   -.02441
  .66662   -.01663
  .71614   -.00705
  .76645    .00167
  .81565    .00804
  .86198    .01155
  .90359    .01198
  .93862    .00990
  .96588    .00655
  .98504    .00323
  .99630    .00086
 1.00000    .00000
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Lednicer format dat file
Selig format dat file

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Polars for NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nlf0215f-il50,000925.9 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0215f-il50,000520.8 at α=11.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0215f-il100,000946.8 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0215f-il100,000549.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0215f-il200,000976.3 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0215f-il200,000576.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0215f-il500,0009110.8 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0215f-il500,0005108.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0215f-il1,000,0009139.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0215f-il1,000,0005131.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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