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NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)

NACA 0010-34 a=0.8 c(li)=0.2 - NACA 0010-34 a=0.8 c(li)=0.2 airfoil


Airfoil naca001034a08cli02-il
Details Dat file Parser  
(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2
NACA 0010-34 a=0.8 c(li)=0.2 airfoil
Max thickness 10% at 40% chord.
Max camber 1.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0010-34 a=0.8 c(li)=0.2
1.00000     0.00100
0.95042     0.01100
0.90076     0.02044
0.80100     0.03700
0.70064     0.04915
0.60031     0.05735
0.49994     0.06186
0.39955     0.06279
0.29917     0.05980
0.19886     0.05172
0.14876     0.04523
0.09875     0.03637
0.07378     0.03094
0.04887     0.02436
0.02407     0.01608
0.01176     0.01062
0.00687     0.00790
0.00000     0.00000
0.00813     -0.00632
0.01324     -0.00820
0.02593     -0.01186
0.05113     -0.01714
0.07622     -0.02122
0.10125     -0.02445
0.15124     -0.02961
0.20114     -0.03312
0.30083     -0.03684
0.40045     -0.03721
0.50006     -0.03526
0.59969     -0.03131
0.69936     -0.02549
0.79900     -0.01830
0.89924     -0.01064
0.94958     -0.00610
1.00000     -0.00100
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Polars for NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca001034a08cli02-il50,000926.5 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001034a08cli02-il50,000530.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001034a08cli02-il100,000947.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001034a08cli02-il100,000546 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001034a08cli02-il200,000967.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001034a08cli02-il200,000562.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001034a08cli02-il500,000989.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001034a08cli02-il500,000573 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001034a08cli02-il1,000,000993.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001034a08cli02-il1,000,000578.7 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
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