Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NLF(1)-0115 (nlf0115-il)

NLF(1)-0115 - NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil


Airfoil nlf0115-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 502 AIRFOILPreviewDetails
NACA 747A315PreviewDetails
AS5045 (15%)PreviewDetails
NACA 5-H-15 AIRFOILPreviewDetails
EPPLER 546 AIRFOILPreviewDetails
NACA 747A415PreviewDetails
WORTMANN FX 79-K-144/17 AIRFOILPreviewDetails
HAWKER TEMPEST 37.5% SEMISPANPreviewDetails
EPPLER 682 AIRFOILPreviewDetails
MB253515 15.0% smoothedPreviewDetails

Polars for NLF(1)-0115 (nlf0115-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nlf0115-il50,000930.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0115-il50,000526.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0115-il100,000945.5 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0115-il100,000541.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0115-il200,000960.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0115-il200,000556 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0115-il500,000981.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0115-il500,000569.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nlf0115-il1,000,000994.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   nlf0115-il1,000,000576.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit