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NACA 65-210 (naca65210-il)

NACA 65-210 - NACA 65-210 airfoil


Airfoil naca65210-il
Details Dat file Parser  
(naca65210-il) NACA 65-210
NACA 65-210 airfoil
Max thickness 10% 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 65-210
1.00000     0.00000
0.95014     0.00622
0.90028     0.01327
0.85038     0.02057
0.80044     0.02783
0.75045     0.03479
0.70043     0.04128
0.65036     0.04712
0.60027     0.05217
0.55014     0.05625
0.50000     0.05915
0.44984     0.06058
0.39968     0.06067
0.34951     0.05954
0.29936     0.05732
0.24921     0.05397
0.19909     0.04938
0.14899     0.04338
0.09894     0.03555
0.07394     0.03069
0.04898     0.02491
0.02408     0.01757
0.01169     0.01273
0.00678     0.00999
0.00435     0.00819
0.00000     0.00000
0.00565     -0.00719
0.00822     -0.00859
0.01331     -0.01059
0.02592     -0.01385
0.05102     -0.01859
0.07606     -0.02221
0.10106     -0.02521
0.15101     -0.02992
0.20091     -0.03346
0.25079     -0.03607
0.30064     -0.03788
0.35049     -0.03894
0.40032     -0.03925
0.45016     -0.03868
0.50000     -0.03709
0.54986     -0.03435
0.59973     -0.03075
0.64964     -0.02652
0.69957     -0.02184
0.74955     -0.01689
0.79956     -0.01191
0.84962     -0.00711
0.89972     -0.00293
0.94986     0.00010
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 65-210 (naca65210-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca65210-il50,000924.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65210-il50,000529.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65210-il100,000943.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65210-il100,000543 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65210-il200,000959 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65210-il200,000550.8 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65210-il500,000972.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65210-il500,000562.7 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65210-il1,000,000982.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65210-il1,000,000569.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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