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NACA 65-206 (naca65206-il)

NACA 65-206 - NACA 65-206 airfoil


Airfoil naca65206-il
Details Dat file Parser  
(naca65206-il) NACA 65-206
NACA 65-206 airfoil
Max thickness 6% at 40% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65-206
1.00000     0.00000
0.95009     0.00511
0.90018     0.01027
0.85024     0.01538
0.80027     0.02029
0.75028     0.02489
0.70026     0.02907
0.65022     0.03276
0.60016     0.03589
0.55009     0.03836
0.50000     0.04003
0.44990     0.04078
0.39981     0.04069
0.34971     0.03982
0.29962     0.03824
0.24953     0.03592
0.19945     0.03277
0.14939     0.02869
0.09936     0.02340
0.07437     0.02012
0.04939     0.01625
0.02444     0.01140
0.01200     0.00822
0.00706     0.00642
0.00460     0.00524
0.00000     0.00000
0.00540     -0.00424
0.00794     -0.00502
0.01300     -0.00608
0.02556     -0.00768
0.05061     -0.00993
0.07563     -0.01164
0.10064     -0.01306
0.15061     -0.01523
0.20055     -0.01685
0.25047     -0.01802
0.30038     -0.01880
0.35029     -0.01922
0.40019     -0.01927
0.45010     -0.01888
0.50000     -0.01797
0.54991     -0.01646
0.59984     -0.01447
0.64978     -0.01216
0.69974     -0.00963
0.74972     -0.00699
0.79973     -0.00437
0.84976     -0.00192
0.89982     0.00007
0.94991     0.00121
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 65-206 (naca65206-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca65206-il50,000922.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65206-il50,000529.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65206-il100,000940.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65206-il100,000539.4 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65206-il200,000954.2 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65206-il200,000550.3 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65206-il500,000971.2 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65206-il500,000556.7 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65206-il1,000,000977.8 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65206-il1,000,000567.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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