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NACA 65(1)-212 a=0.6 (naca651212a06-il)

NACA 65(1)-212 a=0.6 - NACA 65(1)-212 a=0.6 airfoil


Airfoil naca651212a06-il
Details Dat file Parser  
(naca651212a06-il) NACA 65(1)-212 a=0.6
NACA 65(1)-212 a=0.6 airfoil
Max thickness 12% at 40% chord.
Max camber 1.5% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(1)-212 a=0.6
1.00000     0.00000
0.95013     0.00521
0.90036     0.01297
0.85064     0.02173
0.80090     0.03082
0.75112     0.03983
0.70124     0.04842
0.65123     0.05634
0.60094     0.06318
0.55051     0.06856
0.50017     0.07231
0.44983     0.07423
0.39951     0.07444
0.34921     0.07304
0.29894     0.07029
0.24869     0.06611
0.19848     0.06042
0.14833     0.05298
0.09827     0.04330
0.07329     0.03728
0.04837     0.03017
0.02356     0.02113
0.01124     0.01520
0.00638     0.01194
0.00399     0.00982
0.00000     0.00000
0.00601     -0.00852
0.00862     -0.01012
0.01376     -0.01242
0.02644     -0.01625
0.05163     -0.02185
0.07671     -0.02606
0.10173     -0.02956
0.15167     -0.03500
0.20152     -0.03904
0.25131     -0.04197
0.30106     -0.04401
0.35079     -0.04518
0.40049     -0.04550
0.45017     -0.04475
0.49983     -0.04283
0.54949     -0.03968
0.59906     -0.03566
0.64877     -0.03124
0.69876     -0.02640
0.74888     -0.02131
0.79910     -0.01604
0.87936     -0.01085
0.89964     -0.00595
0.94987     -0.00191
1.00000     0.00000
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Selig format dat file

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Polars for NACA 65(1)-212 a=0.6 (naca651212a06-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca651212a06-il50,000925.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651212a06-il50,000529.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651212a06-il100,000946.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651212a06-il100,000545.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651212a06-il200,000966.7 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651212a06-il200,000556.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651212a06-il500,000981.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651212a06-il500,000569.3 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca651212a06-il1,000,000994.1 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca651212a06-il1,000,000575.7 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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