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NACA 8-H-12 AIRFOIL (n8h12-il)

NACA 8-H-12 AIRFOIL - NACA 8-H-12 rotorcraft airfoil


Airfoil n8h12-il
Details Dat file Parser  
(n8h12-il) NACA 8-H-12 AIRFOIL
NACA 8-H-12 rotorcraft airfoil
Max thickness 12% at 30% chord.
Max camber 3.5% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 8-H-12 AIRFOIL
       19.       18.

 0.0000000 0.0000000
 0.0036000 0.0152000
 0.0080000 0.0201000
 0.0198000 0.0294000
 0.0442000 0.0431000
 0.0691000 0.0538000
 0.0943000 0.0626000
 0.1450000 0.0763000
 0.1961000 0.0860000
 0.2475000 0.0924000
 0.2997000 0.0953000
 0.4029000 0.0903000
 0.5039000 0.0767000
 0.6036000 0.0585000
 0.7025000 0.0384000
 0.8011000 0.0189000
 0.9001999 0.0034000
 0.9499000 0.0012000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0114000 -.0095000
 0.0169000 -.0112000
 0.0302000 -.0141000
 0.0558000 -.0174000
 0.0809000 -.0192000
 0.1057000 -.0206000
 0.1550000 -.0224000
 0.2039000 -.0235000
 0.2525000 -.0242000
 0.3003000 -.0245000
 0.3971000 -.0249000
 0.4961000 -.0244000
 0.5964000 -.0229000
 0.7988000 -.0164000
 0.8998001 -.0105000
 0.9500000 -.0063000
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for NACA 8-H-12 AIRFOIL (n8h12-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n8h12-il50,00098 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n8h12-il50,000518.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n8h12-il100,000945.6 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n8h12-il100,000548 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n8h12-il200,000972 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n8h12-il200,000571.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n8h12-il500,0009104.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n8h12-il500,000598.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n8h12-il1,000,0009128.4 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n8h12-il1,000,0005118.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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