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NACA 16009 (naca16009-il)

NACA 16009 - NACA 16009 airfoil


Airfoil naca16009-il
Details Dat file Parser  
(naca16009-il) NACA 16009
NACA 16009 airfoil
Max thickness 9% at 50% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 16009
1.00000     0.00090
0.99893     0.00111
0.99572     0.00176
0.99039     0.00283
0.98296     0.00431
0.97347     0.00618
0.96194     0.00839
0.94844     0.01089
0.93301     0.01359
0.91573     0.01644
0.89668     0.01938
0.87592     0.02237
0.85355     0.02534
0.82967     0.02825
0.80438     0.03103
0.77779     0.03364
0.75000     0.03603
0.72114     0.03817
0.69134     0.04003
0.66072     0.04159
0.62941     0.04286
0.59755     0.04382
0.56526     0.04449
0.53270     0.04488
0.50000     0.04500
0.46730     0.04488
0.43474     0.04453
0.40245     0.04396
0.37059     0.04317
0.33928     0.04218
0.30866     0.04100
0.27886     0.03965
0.25000     0.03814
0.22221     0.03648
0.19562     0.03467
0.17033     0.03274
0.14645     0.03070
0.12408     0.02855
0.10332     0.02632
0.08427     0.02401
0.06699     0.02158
0.05156     0.01908
0.03806     0.01649
0.02653     0.01375
0.01704     0.01098
0.00961     0.00814
0.00428     0.00534
0.00107     0.00267
0.00000     0.00000
0.00107     -0.00267
0.00428     -0.00534
0.00961     -0.00814
0.01704     -0.01098
0.02653     -0.01375
0.03806     -0.01649
0.05156     -0.01908
0.06699     -0.02158
0.08427     -0.02401
0.10332     -0.02632
0.12408     -0.02855
0.14645     -0.03070
0.17033     -0.03274
0.19562     -0.03467
0.22221     -0.03648
0.25000     -0.03814
0.27886     -0.03965
0.30866     -0.04100
0.33928     -0.04218
0.37059     -0.04317
0.40245     -0.04396
0.43474     -0.04453
0.46730     -0.04488
0.50000     -0.04500
0.53270     -0.04488
0.56526     -0.04449
0.59755     -0.04382
0.62941     -0.04286
0.66072     -0.04159
0.69134     -0.04003
0.72114     -0.03817
0.75000     -0.03603
0.77779     -0.03364
0.80438     -0.03103
0.82967     -0.02825
0.85355     -0.02534
0.87592     -0.02237
0.89668     -0.01938
0.91573     -0.01644
0.93301     -0.01359
0.94844     -0.01089
0.96194     -0.00839
0.97347     -0.00618
0.98296     -0.00431
0.99039     -0.00283
0.99572     -0.00176
0.99893     -0.00111
1.00000     -0.00090
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Lednicer format dat file
Selig format dat file

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Polars for NACA 16009 (naca16009-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16009-il50,000918 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16009-il50,000519.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16009-il100,000925.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16009-il100,000528.8 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16009-il200,000939.4 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16009-il200,000534.6 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16009-il500,000944.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16009-il500,000538 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16009-il1,000,000947 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16009-il1,000,000547.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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