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-CL3-152 (fx73cl3152-il)

FX 73-CL3-152 - Wortmann FX 73-CL3-152 airfoil


Airfoil fx73cl3152-il
Details Dat file Parser  
(fx73cl3152-il) FX 73-CL3-152
Wortmann FX 73-CL3-152 airfoil
Max thickness 15.2% at 22.2% chord.
Max camber 8% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 73-CL3-152
1.00000     0.00000
0.99893     0.00058
0.99572     0.00171
0.99039     0.00346
0.98296     0.00581
0.97347     0.00879
0.96194     0.01239
0.94844     0.01664
0.93301     0.02150
0.91573     0.02698
0.89668     0.03313
0.87592     0.03994
0.85355     0.04733
0.82967     0.05516
0.80438     0.06330
0.77779     0.07157
0.75000     0.07964
0.72114     0.08726
0.69134     0.09440
0.66072     0.10120
0.62941     0.10776
0.59755     0.11408
0.56526     0.12012
0.53270     0.12584
0.50000     0.13119
0.46730     0.13608
0.43474     0.14045
0.40245     0.14420
0.37059     0.14721
0.33928     0.14920
0.30866     0.14976
0.27886     0.14872
0.25000     0.14611
0.22221     0.14212
0.19562     0.13681
0.17033     0.13009
0.14645     0.12209
0.12408     0.11308
0.10332     0.10337
0.08427     0.09316
0.06699     0.08255
0.05156     0.07165
0.03806     0.06054
0.02653     0.04932
0.01704     0.03831
0.00961     0.02763
0.00428     0.01748
0.00107     0.00831
0.00000     0.00000
0.00107     -0.00740
0.00428     -0.01391
0.00961     -0.01934
0.01704     -0.02312
0.02653     -0.02551
0.03806     -0.02689
0.05156     -0.02750
0.06699     -0.02751
0.08427     -0.02684
0.10332     -0.02548
0.12408     -0.02344
0.14645     -0.02081
0.17033     -0.01765
0.19562     -0.01404
0.22221     -0.01005
0.25000     -0.00583
0.27886     -0.00150
0.30866     0.00288
0.33928     0.00728
0.37059     0.01162
0.40245     0.01581
0.43474     0.01975
0.46730     0.02340
0.50000     0.02674
0.53270     0.02973
0.56526     0.03229
0.59755     0.03437
0.62941     0.03591
0.66072     0.03684
0.69134     0.03715
0.72114     0.03671
0.75000     0.03536
0.77779     0.03306
0.80438     0.03002
0.82967     0.02657
0.85355     0.02308
0.87592     0.01965
0.89668     0.01630
0.91573     0.01311
0.93301     0.01012
0.94844     0.00745
0.96194     0.00515
0.97347     0.00319
0.98296     0.00162
0.99039     0.00050
0.99572     -0.00015
0.99893     -0.00028
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 227 (MVA H.37) AIRFOILPreviewDetails
EPPLER 421 AIRFOILPreviewDetails
GOE 441 AIRFOILPreviewDetails
FX 73-CL2-152PreviewDetails
USA 31 AIRFOILPreviewDetails
USA 32 AIRFOILPreviewDetails
GOE 226 (MVA H.36) AIRFOILPreviewDetails
GOE 592 AIRFOILPreviewDetails
GOE 503 AIRFOILPreviewDetails
GOE 242 (MVA PR.2) AIRFOILPreviewDetails

Polars for FX 73-CL3-152 (fx73cl3152-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx73cl3152-il50,00095.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl3152-il50,000528.4 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl3152-il100,000938.4 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl3152-il100,000550.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl3152-il200,000964 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl3152-il200,000571 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl3152-il500,000999.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl3152-il500,0005100.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx73cl3152-il1,000,0009129.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx73cl3152-il1,000,0005128.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit