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NACA 63012A AIRFOIL (n63012a-il)

NACA 63012A AIRFOIL - NACA 63-012A airfoil


Airfoil n63012a-il
Details Dat file Parser  
(n63012a-il) NACA 63012A AIRFOIL
NACA 63-012A airfoil
Max thickness 12% at 35% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NACA 63012A AIRFOIL
   26.0000   26.0000

  0.000000  0.000000
  0.005000  0.009730
  0.007500  0.011730
  0.012500  0.014920
  0.025000  0.020780
  0.050000  0.028950
  0.075000  0.035040
  0.100000  0.039940
  0.150000  0.047470
  0.200000  0.052870
  0.250000  0.056640
  0.300000  0.059010
  0.350000  0.059950
  0.400000  0.059570
  0.450000  0.057920
  0.500000  0.055170
  0.550000  0.051480
  0.600000  0.047000
  0.650000  0.041860
  0.700000  0.036210
  0.750000  0.030260
  0.800000  0.024260
  0.850000  0.018260
  0.900000  0.012250
  0.950000  0.006250
  1.000000  0.000250

  0.000000  0.000000
  0.005000 -0.009730
  0.007500 -0.011730
  0.012500 -0.014920
  0.025000 -0.020780
  0.050000 -0.028950
  0.075000 -0.035040
  0.100000 -0.039940
  0.150000 -0.047470
  0.200000 -0.052870
  0.250000 -0.056640
  0.300000 -0.059010
  0.350000 -0.059950
  0.400000 -0.059570
  0.450000 -0.057920
  0.500000 -0.055170
  0.550000 -0.051480
  0.600000 -0.047000
  0.650000 -0.041860
  0.700000 -0.036210
  0.750000 -0.030260
  0.800000 -0.024260
  0.850000 -0.018260
  0.900000 -0.012250
  0.950000 -0.006250
  1.000000 -0.000250
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Lednicer format dat file
Selig format dat file

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Polars for NACA 63012A AIRFOIL (n63012a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n63012a-il50,000928.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63012a-il50,000528.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n63012a-il100,000941.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63012a-il100,000538.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n63012a-il200,000952 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n63012a-il200,000541.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n63012a-il500,000958.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n63012a-il500,000554.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n63012a-il1,000,000964.7 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n63012a-il1,000,000566.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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