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NACA 63(3)-618 (naca633618-il)

NACA 63(3)-618 - NACA 63(3)-618 airfoil


Airfoil naca633618-il
Details Dat file Parser  
(naca633618-il) NACA 63(3)-618
NACA 63(3)-618 airfoil
Max thickness 18% at 34.7% chord.
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(3)-618
1.00000     0.00000
0.95048     0.01293
0.90103     0.02531
0.85147     0.03800
0.80178     0.05073
0.75191     0.06330
0.70187     0.07534
0.65164     0.08655
0.60125     0.09667
0.55069     0.10541
0.50000     0.11251
0.44919     0.11767
0.39829     0.12056
0.34734     0.12086
0.29640     0.11822
0.24549     0.11273
0.19469     0.10418
0.14404     0.09219
0.09367     0.07586
0.06868     0.06542
0.04393     0.05268
0.01965     0.03616
0.00797     0.02491
0.00361     0.01878
0.00156     0.01511
0.00000     0.00000
0.00844     -0.01211
0.01139     -0.01458
0.01703     -0.01849
0.03035     -0.02500
0.05607     -0.03372
0.08132     -0.03998
0.10633     -0.04484
0.15596     -0.05181
0.20531     -0.05642
0.25451     -0.05903
0.30360     -0.05990
0.35266     -0.05906
0.40171     -0.05630
0.45081     -0.05197
0.50000     -0.04633
0.54931     -0.03971
0.59875     -0.03241
0.64836     -0.02475
0.69813     -0.01702
0.74809     -0.00960
0.79822     -0.00297
0.84853     0.00238
0.89897     0.00571
0.94952     0.00603
1.00000     0.00000
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Selig format dat file

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Polars for NACA 63(3)-618 (naca633618-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca633618-il50,00095.1 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633618-il50,000514.2 at α=12.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633618-il100,000941.6 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633618-il100,000546.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633618-il200,000974 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633618-il200,000573.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633618-il500,0009107.6 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633618-il500,0005102.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633618-il1,000,0009133.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633618-il1,000,0005122.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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