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NACA 1410 (naca1410-il)

NACA 1410 - NACA 1410 airfoil


Airfoil naca1410-il
Details Dat file Parser  
(naca1410-il) NACA 1410
NACA 1410 airfoil
Max thickness 10% at 29.9% chord.
Max camber 1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 1410
1.00000     0.00105
0.95021     0.00832
0.90034     0.01513
0.80049     0.02741
0.70051     0.03804
0.60042     0.04692
0.50025     0.05385
0.40000     0.05836
0.29937     0.05940
0.24907     0.05809
0.19880     0.05531
0.14861     0.05062
0.09854     0.04338
0.07358     0.03837
0.04870     0.03194
0.02398     0.02297
0.01174     0.01639
0.00000     0.00000
0.01326     -0.01515
0.02602     -0.02055
0.05130     -0.02726
0.07642     -0.03157
0.10146     -0.03462
0.15139     -0.03844
0.20120     -0.04031
0.25093     -0.04091
0.30063     -0.04064
0.40000     -0.03936
0.49975     -0.03439
0.59958     -0.02914
0.69949     -0.02304
0.79951     -0.01629
0.89966     -0.00901
0.94979     -0.00512
1.00000     -0.00105
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Polars for NACA 1410 (naca1410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca1410-il50,000931.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1410-il50,000531.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1410-il100,000944.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1410-il100,000542.2 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1410-il200,000956.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1410-il200,000550.6 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1410-il500,000970.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1410-il500,000563.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1410-il1,000,000978.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1410-il1,000,000578.3 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
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