Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 73-CL1-152 (fx73cl1152-il)

FX 73-CL1-152 - Wortmann FX 73-CL1-152 airfoil


Airfoil fx73cl1152-il
Details Dat file Parser  
(fx73cl1152-il) FX 73-CL1-152
Wortmann FX 73-CL1-152 airfoil
Max thickness 15.2% at 22.2% chord.
Max camber 6.1% at 33.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 73-CL1-152
1.00000     0.00000
0.99893     0.00066
0.99572     0.00180
0.99039     0.00335
0.98296     0.00531
0.97347     0.00762
0.96194     0.01025
0.94844     0.01320
0.93301     0.01644
0.91573     0.01997
0.89668     0.02387
0.87592     0.02815
0.85355     0.03279
0.82967     0.03772
0.80438     0.04294
0.77779     0.04848
0.75000     0.05432
0.72114     0.06043
0.69134     0.06675
0.66072     0.07327
0.62941     0.07993
0.59755     0.08667
0.56526     0.09342
0.53270     0.10009
0.50000     0.10658
0.46730     0.11278
0.43474     0.11856
0.40245     0.12380
0.37059     0.12833
0.33928     0.13184
0.30866     0.13392
0.27886     0.13434
0.25000     0.13311
0.22221     0.13043
0.19562     0.12631
0.17033     0.12067
0.14645     0.11363
0.12408     0.10547
0.10332     0.09648
0.08427     0.08687
0.06699     0.07673
0.05156     0.06625
0.03806     0.05574
0.02653     0.04533
0.01704     0.03513
0.00961     0.02525
0.00428     0.01607
0.00107     0.00778
0.00000     0.00000
0.00107     -0.00756
0.00428     -0.01485
0.00961     -0.02115
0.01704     -0.02595
0.02653     -0.02925
0.03806     -0.03132
0.05156     -0.03252
0.06699     -0.03293
0.08427     -0.03276
0.10332     -0.03207
0.12408     -0.03091
0.14645     -0.02928
0.17033     -0.02709
0.19562     -0.02454
0.22221     -0.02175
0.25000     -0.01882
0.27886     -0.01589
0.30866     -0.01296
0.33928     -0.01008
0.37059     -0.00726
0.40245     -0.00460
0.43474     -0.00215
0.46730     0.00009
0.50000     0.00214
0.53270     0.00398
0.56526     0.00560
0.59755     0.00697
0.62941     0.00808
0.66072     0.00892
0.69134     0.00950
0.72114     0.00988
0.75000     0.01004
0.77779     0.00997
0.80438     0.00965
0.82967     0.00915
0.85355     0.00852
0.87592     0.00777
0.89668     0.00694
0.91573     0.00602
0.93301     0.00505
0.94844     0.00403
0.96194     0.00301
0.97347     0.00201
0.98296     0.00111
0.99039     0.00039
0.99572     -0.00006
0.99893     -0.00020
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 73-CL2-152PreviewDetails
EPPLER 1210 AIRFOILPreviewDetails
Glenn Martin 4PreviewDetails
GOE 711 AIRFOILPreviewDetails
GOE 675 AIRFOILPreviewDetails
GOE 744 AIRFOILPreviewDetails
GOE 481A AIRFOILPreviewDetails
GOE 505 AIRFOILPreviewDetails
GOE 387 AIRFOILPreviewDetails
AUGUST 160PreviewDetails

Polars for FX 73-CL1-152 (fx73cl1152-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx73cl1152-il50,00094.9 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl1152-il50,000520.7 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl1152-il100,000924.5 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl1152-il100,000542.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl1152-il200,000953.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl1152-il200,000568.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl1152-il500,0009100.8 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl1152-il500,0005106.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl1152-il1,000,0009137.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl1152-il1,000,0005136.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit