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FX 74-CL6-140 (fx74cl6140-il)

FX 74-CL6-140 - Wortmann FX 74-CL6-140 airfoil


Airfoil fx74cl6140-il
Details Dat file Parser  
(fx74cl6140-il) FX 74-CL6-140
Wortmann FX 74-CL6-140 airfoil
Max thickness 14.1% at 30.9% chord.
Max camber 7.1% at 33.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 74-CL6-140
1.00000     0.00000
0.99893     0.00037
0.99572     0.00164
0.99039     0.00342
0.98296     0.00574
0.97347     0.00846
0.96194     0.01154
0.94844     0.01496
0.93301     0.01869
0.91573     0.02277
0.89668     0.02724
0.87592     0.03213
0.85355     0.03742
0.82967     0.04303
0.80438     0.04892
0.77779     0.05513
0.75000     0.06159
0.72114     0.06828
0.69134     0.07517
0.66072     0.08219
0.62941     0.08933
0.59755     0.09654
0.56526     0.10379
0.53270     0.11100
0.50000     0.11809
0.46730     0.12491
0.43474     0.13110
0.40245     0.13615
0.37059     0.13958
0.33928     0.14115
0.30866     0.14093
0.27886     0.13910
0.25000     0.13580
0.22221     0.13115
0.19562     0.12525
0.17033     0.11826
0.14645     0.11037
0.12408     0.10174
0.10332     0.09250
0.08427     0.08281
0.06699     0.07280
0.05156     0.06262
0.03806     0.05247
0.02653     0.04259
0.01704     0.03304
0.00961     0.02402
0.00428     0.01533
0.00107     0.00701
0.00000     0.00000
0.00107     -0.00514
0.00428     -0.00819
0.00961     -0.00993
0.01704     -0.01115
0.02653     -0.01188
0.03806     -0.01223
0.05156     -0.01220
0.06699     -0.01181
0.08427     -0.01106
0.10332     -0.01003
0.12408     -0.00886
0.14645     -0.00759
0.17033     -0.00627
0.19562     -0.00491
0.22221     -0.00353
0.25000     -0.00217
0.27886     -0.00086
0.30866      0.00039
0.33928     0.00157
0.37059     0.00267
0.40245     0.00371
0.43474     0.00471
0.46730     0.00571
0.50000     0.00679
0.53270     0.00795
0.56526     0.00927
0.59755     0.01088
0.62941     0.01285
0.66072     0.01507
0.69134     0.01722
0.72114     0.01899
0.75000     0.02016
0.77779     0.02069
0.80438     0.02062
0.82967     0.02001
0.85355     0.01890
0.87592     0.01736
0.89668     0.01553
0.91573     0.01349
0.93301     0.01135
0.94844     0.00913
0.96194     0.00696
0.97347     0.00497
0.98296     0.00326
0.99039     0.00188
0.99572     0.00087
0.99893     0.00020
1.00000     0.00000
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Selig format dat file

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Polars for FX 74-CL6-140 (fx74cl6140-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx74cl6140-il50,00095.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74cl6140-il50,000518.9 at α=0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74cl6140-il100,000919.9 at α=-0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74cl6140-il100,000540.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74cl6140-il200,000948.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74cl6140-il200,000572 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74cl6140-il500,0009114.8 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74cl6140-il500,0005120.5 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx74cl6140-il1,000,0009157.9 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx74cl6140-il1,000,0005158.6 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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