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NACA 66(1)-212 (naca661212-il)

NACA 66(1)-212 - NACA 66(1)-212 airfoil


Airfoil naca661212-il
Details Dat file Parser  
(naca661212-il) NACA 66(1)-212
NACA 66(1)-212 airfoil
Max thickness 12% at 45% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66(1)-212
1.00000     0.00000
0.95022     0.00789
0.90043     0.01750
0.85057     0.02755
0.80065     0.03739
0.75066     0.04661
0.70061     0.05487
0.65051     0.06169
0.60036     0.06659
0.55019     0.06931
0.50000     0.07068
0.44981     0.07095
0.39962     0.07018
0.34943     0.06833
0.29925     0.06539
0.24908     0.06132
0.19894     0.05596
0.14883     0.04905
0.09878     0.04011
0.07379     0.03459
0.04883     0.02809
0.02395     0.01991
0.01156     0.01462
0.00666     0.01154
0.00424     0.00953
0.00000     0.00000
0.00576     -0.00853
0.00834     -0.01014
0.01344     -0.01248
0.02605     -0.01619
0.05117     -0.02177
0.07621     -0.02611
0.10122     -0.02977
0.15117     -0.03559
0.20106     -0.04004
0.25092     -0.04342
0.30075     -0.04595
0.35057     -0.04773
0.40038     -0.04876
0.45019     -0.04905
0.50000     -0.04862
0.54981     -0.04741
0.59964     -0.04517
0.64949     -0.04109
0.69939     -0.03543
0.74934     -0.02871
0.79935     -0.02147
0.84943     -0.01409
0.89957     -0.00716
0.94978     -0.00157
1.00000     0.00000
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Selig format dat file

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Polars for NACA 66(1)-212 (naca661212-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca661212-il50,000922 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca661212-il50,000522.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca661212-il100,000937.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca661212-il100,000532.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca661212-il200,000947.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca661212-il200,000546.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca661212-il500,000971.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca661212-il500,000562.8 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca661212-il1,000,000986 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca661212-il1,000,000570.5 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
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