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NACA 66-021 AIRFOIL (n66021-il)

NACA 66-021 AIRFOIL - NACA 66(4)-021 airfoil


Airfoil n66021-il
Details Dat file Parser  
(n66021-il) NACA 66-021 AIRFOIL
NACA 66(4)-021 airfoil
Max thickness 21% at 45% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 66-021 AIRFOIL
       26.       26.

  0.000000  0.000000
  0.005000  0.015250
  0.007500  0.018040
  0.012500  0.022400
  0.025000  0.030450
  0.050000  0.042690
  0.075000  0.052330
  0.100000  0.060520
  0.150000  0.073690
  0.200000  0.083760
  0.250000  0.091530
  0.300000  0.097380
  0.350000  0.101540
  0.400000  0.104070
  0.450000  0.105000
  0.500000  0.104340
  0.550000  0.101860
  0.600000  0.096920
  0.650000  0.087930
  0.700000  0.076100
  0.750000  0.062510
  0.800000  0.047960
  0.850000  0.033240
  0.900000  0.019240
  0.950000  0.007170
  1.000000  0.000000

  0.000000  0.000000
  0.005000 -0.015250
  0.007500 -0.018040
  0.012500 -0.022400
  0.025000 -0.030450
  0.050000 -0.042690
  0.075000 -0.052330
  0.100000 -0.060520
  0.150000 -0.073690
  0.200000 -0.083760
  0.250000 -0.091530
  0.300000 -0.097380
  0.350000 -0.101540
  0.400000 -0.104070
  0.450000 -0.105000
  0.500000 -0.104340
  0.550000 -0.101860
  0.600000 -0.096920
  0.650000 -0.087930
  0.700000 -0.076100
  0.750000 -0.062510
  0.800000 -0.047960
  0.850000 -0.033240
  0.900000 -0.019240
  0.950000 -0.007170
  1.000000  0.000000
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Lednicer format dat file
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Polars for NACA 66-021 AIRFOIL (n66021-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n66021-il50,000918.6 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n66021-il50,000511 at α=13.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n66021-il100,000923.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n66021-il100,000515.4 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n66021-il200,000925.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n66021-il200,000526.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n66021-il500,000957.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n66021-il500,000554.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n66021-il1,000,000978.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   n66021-il1,000,000564.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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