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NACA 67 (naca671215-il)

NACA 67 - NACA 67


Airfoil naca671215-il
Details Dat file Parser  
(naca671215-il) NACA 67
NACA 67
Max thickness 15% at 50% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 67,1-215
1.00000     0.00000
0.95037     0.01103
0.90071     0.02537
0.85092     0.03999
0.80100     0.05335
0.75098     0.06515
0.70086     0.07373
0.65068     0.07935
0.60047     0.08302
0.55024     0.08516
0.50000     0.08600
0.44976     0.08570
0.39953     0.08430
0.34930     0.08185
0.29908     0.07825
0.24887     0.07348
0.19869     0.06735
0.14854     0.05954
0.09845     0.04947
0.07344     0.04321
0.04848     0.03557
0.02361     0.02577
0.01128     0.01867
0.00642     0.01460
0.00402     0.01213
0.00000     0.00000
0.00598     -0.01113
0.00858     -0.01320
0.01372     -0.01653
0.02639     -0.02205
0.05152     -0.02925
0.07656     -0.03473
0.10155     -0.03913
0.15146     -0.04608
0.20131     -0.05143
0.25113     -0.05558
0.30092     -0.05881
0.35070     -0.06125
0.40047     -0.06288
0.45024     -0.06380
0.50000     -0.06394
0.54976     -0.06326
0.59953     -0.06160
0.64932     -0.05875
0.69914     -0.05429
0.74902     -0.04725
0.79900     -0.03743
0.84908     -0.02653
0.89929     -0.01503
0.94963     -0.00471
1.00000     0.00000
Dat file parser warnings
  • Line 2 - Invalid characters : 1-215
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Lednicer format dat file
Selig format dat file

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Polars for NACA 67 (naca671215-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca671215-il50,000923.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca671215-il50,000521.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca671215-il100,000934.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca671215-il100,000525.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca671215-il200,000942.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca671215-il200,000533.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca671215-il500,000956.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca671215-il500,000555.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca671215-il1,000,000984.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca671215-il1,000,000571.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
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