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NACA 65(2)-215 (naca652215-il)

NACA 65(2)-215 - NACA 65(2)-215 airfoil


Airfoil naca652215-il
Details Dat file Parser  
(naca652215-il) NACA 65(2)-215
NACA 65(2)-215 airfoil
Max thickness 15% 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(2)-215
1.00000     0.00000
0.95020     0.00744
0.90040     0.01660
0.85055     0.02649
0.80063     0.03653
0.75065     0.04638
0.70062     0.05572
0.65053     0.06433
0.60069     0.07189
0.55021     0.07815
0.50000     0.08271
0.44976     0.08522
0.39952     0.08569
0.34927     0.08426
0.29904     0.08123
0.24882     0.07658
0.19863     0.07018
0.14848     0.06175
0.09841     0.05069
0.07342     0.04380
0.04848     0.03557
0.02365     0.02506
0.01132     0.01805
0.00645     0.01422
0.00406     0.01170
0.00000     0.00000
0.00594     -0.01070
0.00855     -0.01282
0.01368     -0.01591
0.02635     -0.02134
0.05152     -0.02925
0.07658     -0.03532
0.10159     -0.04035
0.15152     -0.04829
0.20137     -0.05426
0.25118     -0.05868
0.30096     -0.06179
0.35073     -0.06366
0.40048     -0.06427
0.45024     -0.06332
0.50000     -0.06065
0.54979     -0.05625
0.59961     -0.05047
0.64947     -0.04373
0.69938     -0.03628
0.74935     -0.02848
0.79937     -0.02061
0.84945     -0.01303
0.89960     -0.00626
0.94980     -0.00112
1.00000     0.00000
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Selig format dat file

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Polars for NACA 65(2)-215 (naca652215-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca652215-il50,000922.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652215-il50,000523.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652215-il100,000946.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652215-il100,000539.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652215-il200,000957.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652215-il200,000555.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652215-il500,000982.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652215-il500,000571.4 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652215-il1,000,000996.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652215-il1,000,000579 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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