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NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il)

NASA/LANGLEY NLF(1)-0416 AIRFOIL - NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil


Airfoil nlf416-il
Details Dat file Parser  
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL
NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil
Max thickness 15.9% at 30.4% chord.
Max camber 2.5% at 34.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 
 NASA/LANGLEY NLF(1)-0416 AIRFOIL
33.        30.
 
 0.00000   0.00000
  .00049    .00403
  .00509    .01446
  .01393    .02573
  .02687    .03729
  .04383    .04870
  .06471    .05964
  .08936    .06984
  .11761    .07904
  .14925    .08707
  .18404    .09374
  .22169    .09892
  .26187    .10247
  .30422    .10425
  .34839    .10405
  .39438    .10162
  .44227    .09729
  .49172    .09166
  .54204    .08515
  .59256    .07801
  .64262    .07047
  .69155    .06272
  .73872    .05493
  .78350    .04724
  .82530    .03977
  .86357    .03265
  .89779    .02594
  .92749    .01974
  .95224    .01400
  .97197    .00862
  .98686    .00398
  .99656    .00098
 1.00000    .00000
 
 0.00000   0.00000
  .00073   -.00439
  .00709   -.01154
  .01956   -.01883
  .03708   -.02594
  .05933   -.03254
  .08609   -.03847
  .11708   -.04361
  .15200   -.04787
  .19050   -.05121
  .23218   -.05357
  .27659   -.05494
  .32326   -.05529
  .37167   -.05462
  .42127   -.05291
  .47150   -.05009
  .52175   -.04614
  .57122   -.04063
  .62019   -.03250
  .67014   -.02231
  .72107   -.01221
  .77156   -.00364
  .82012    .00278
  .86536    .00667
  .90576    .00792
  .93978    .00696
  .96638    .00478
  .98520    .00242
  .99633    .00065
 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)-0416 AIRFOIL (nlf416-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nlf416-il50,000914.8 at α=0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf416-il50,000525.7 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf416-il100,000945.1 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf416-il100,000548.3 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf416-il200,000965.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf416-il200,000567.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf416-il500,000993.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf416-il500,000591.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf416-il1,000,0009115.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf416-il1,000,0005108.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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