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NACA 65-410 (naca65410-il)

NACA 65-410 - NACA 65-410 airfoil


Airfoil naca65410-il
Details Dat file Parser  
(naca65410-il) NACA 65-410
NACA 65-410 airfoil
Max thickness 10% at 39.9% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65-410
1.00000     0.00000
0.95029     0.00937
0.90057     0.01842
0.85076     0.02729
0.80088     0.03577
0.75090     0.04372
0.70085     0.05099
0.65073     0.05741
0.60053     0.06288
0.55029     0.06720
0.50000     0.07018
0.44968     0.07153
0.39936     0.07138
0.34903     0.06983
0.29872     0.06702
0.24843     0.06290
0.19817     0.05731
0.14798     0.05006
0.09788     0.04067
0.07289     0.03487
0.04797     0.02800
0.02318     0.01935
0.01089     0.01372
0.00607     0.01061
0.00372     0.00861
0.00000     0.00000
0.00628     -0.00661
0.00893     -0.00781
0.01411     -0.00944
0.02682     -0.01191
0.05203     -0.01536
0.07711     -0.01791
0.10212     -0.01999
0.15202     -0.02314
0.20183     -0.02547
0.25157     -0.02710
0.30128     -0.02814
0.35097     -0.02863
0.40064     -0.02854
0.45032     -0.02773
0.50000     -0.02606
0.54971     -0.02340
0.59947     -0.02004
0.64927     -0.01621
0.69915     -0.01211
0.74910     -0.00792
0.79912     -0.00393
0.84924     -0.00037
0.89943     0.00226
0.94971     0.00327
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 65-410 (naca65410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca65410-il50,000928.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65410-il50,000535.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65410-il100,000952.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65410-il100,000552.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65410-il200,000975.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65410-il200,000568.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65410-il500,000997.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65410-il500,000587.5 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65410-il1,000,0009114.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65410-il1,000,000598.9 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
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