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FX 73-CL2-152 (fx73cl2152-il)

FX 73-CL2-152 - Wortmann FX 73-CL2-152 airfoil


Airfoil fx73cl2152-il
Details Dat file Parser  
(fx73cl2152-il) FX 73-CL2-152
Wortmann FX 73-CL2-152 airfoil
Max thickness 15.2% at 22.2% chord.
Max camber 6.6% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 73-CL2-152
1.00000     0.00000
0.99893     0.00138
0.99572     0.00394
0.99039     0.00715
0.98296     0.01103
0.97347     0.01540
0.96194     0.02014
0.94844     0.02514
0.93301     0.03036
0.91573     0.03576
0.89668     0.04127
0.87592     0.04686
0.85355     0.05249
0.82967     0.05817
0.80438     0.06386
0.77779     0.06955
0.75000     0.07523
0.72114     0.08090
0.69134     0.08650
0.66072     0.09204
0.62941     0.09751
0.59755     0.10288
0.56526     0.10811
0.53270     0.11316
0.50000     0.11798
0.46730     0.12249
0.43474     0.12661
0.40245     0.13027
0.37059     0.13335
0.33928     0.13555
0.30866     0.13648
0.27886     0.13591
0.25000     0.13390
0.22221     0.13064
0.19562     0.12616
0.17033     0.12037
0.14645     0.11336
0.12408     0.10539
0.10332     0.09677
0.08427     0.08768
0.06699     0.07820
0.05156     0.06848
0.03806     0.05854
0.02653     0.04839
0.01704     0.03798
0.00961     0.02745
0.00428     0.01727
0.00107     0.00800
0.00000     0.00000
0.00107     -0.00697
0.00428     -0.01319
0.00961     -0.01865
0.01704     -0.02304
0.02653     -0.02623
0.03806     -0.02846
0.05156     -0.03003
0.06699     -0.03113
0.08427     -0.03174
0.10332     -0.03175
0.12408     -0.03102
0.14645     -0.02955
0.17033     -0.02739
0.19562     -0.02468
0.22221     -0.02153
0.25000     -0.01803
0.27886     -0.01431
0.30866     -0.01041
0.33928     -0.00637
0.37059     -0.00224
0.40245     0.00188
0.43474     0.00591
0.46730     0.00980
0.50000     0.01353
0.53270     0.01705
0.56526     0.02028
0.59755     0.02317
0.62941     0.02565
0.66072     0.02769
0.69134     0.02925
0.72114     0.03035
0.75000     0.03096
0.77779     0.03103
0.80438     0.03057
0.82967     0.02959
0.85355     0.02823
0.87592     0.02652
0.89668     0.02437
0.91573     0.02184
0.93301     0.01898
0.94844     0.01597
0.96194     0.01290
0.97347     0.00980
0.98296     0.00684
0.99039     0.00418
0.99572     0.00208
0.99893     0.00051
1.00000     0.00000
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Polars for FX 73-CL2-152 (fx73cl2152-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx73cl2152-il50,000916.3 at α=0°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl2152-il50,000532.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl2152-il100,000941.3 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl2152-il100,000552.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl2152-il200,000966.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl2152-il200,000574.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl2152-il500,0009104.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl2152-il500,0005107.8 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl2152-il1,000,0009136.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl2152-il1,000,0005135.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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