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NACA 63-412 AIRFOIL (n63412-il)

NACA 63-412 AIRFOIL - NACA 63(1)-412 airfoil


Airfoil n63412-il
Details Dat file Parser  
(n63412-il) NACA 63-412 AIRFOIL
NACA 63(1)-412 airfoil
Max thickness 12% at 34.9% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 63-412 AIRFOIL
      26.       26.

  0.000000  0.000000
  0.003360  0.010710
  0.005670  0.013200
  0.010410  0.017190
  0.022570  0.024600
  0.047270  0.035440
  0.072180  0.043790
  0.097180  0.050630
  0.147350  0.061380
  0.197650  0.069290
  0.248000  0.074990
  0.298400  0.078720
  0.348820  0.080590
  0.399240  0.080620
  0.449640  0.078940
  0.500000  0.075670
  0.550310  0.071250
  0.600570  0.065620
  0.650760  0.058990
  0.700870  0.051530
  0.750890  0.043440
  0.800840  0.034920
  0.850700  0.026180
  0.900490  0.017390
  0.950230  0.008810
  1.000000  0.000000

  0.000000  0.000000
  0.006640 -0.008710
  0.009330 -0.010400
  0.014590 -0.012910
  0.027430 -0.017160
  0.052730 -0.022800
  0.077820 -0.026850
  0.102820 -0.029950
  0.152650 -0.034460
  0.202350 -0.037450
  0.252000 -0.039190
  0.301600 -0.039840
  0.351118 -0.039390
  0.400760 -0.037780
  0.450350 -0.035140
  0.500000 -0.031640
  0.549690 -0.027450
  0.599430 -0.022780
  0.649240 -0.017990
  0.699130 -0.012650
  0.749110 -0.007640
  0.799160 -0.003080
  0.849300  0.000740
  0.899510  0.003290
  0.949770  0.003300
  1.000000  0.000000
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Lednicer format dat file
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Polars for NACA 63-412 AIRFOIL (n63412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n63412-il50,000936.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n63412-il50,000536 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   n63412-il100,000956.6 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63412-il100,000554.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n63412-il200,000977.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n63412-il200,000570.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n63412-il500,000999.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63412-il500,000588.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n63412-il1,000,0009115.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n63412-il1,000,000598.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
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