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

FX 83-W-227 (fx83w227-il)

FX 83-W-227 - Wortmann FX 83-W-227 airfoil for use on wind turbines (W)


Airfoil fx83w227-il
Details Dat file Parser  
(fx83w227-il) FX 83-W-227
Wortmann FX 83-W-227 airfoil for use on wind turbines (W)
Max thickness 22.6% at 33.9% chord.
Max camber 3.4% at 40.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 83-W-227
1.00000     0.00000
0.99893     0.00058
0.99572     0.00142
0.99039     0.00324
0.98296     0.00590
0.97347     0.00950
0.96194     0.01391
0.94844     0.01901
0.93301     0.02471
0.91573     0.03090
0.89668     0.03753
0.87592     0.04450
0.85355     0.05176
0.82967     0.05928
0.80438     0.06704
0.77779     0.07501
0.75000     0.08310
0.72114     0.09119
0.69134     0.09916
0.66072     0.10689
0.62941     0.11425
0.59755     0.12114
0.56526     0.12744
0.53270     0.13306
0.50000     0.13784
0.46730     0.14169
0.43474     0.14455
0.40245     0.14640
0.37059     0.14720
0.33928     0.14690
0.30866     0.14546
0.27886     0.14286
0.25000     0.13911
0.22221     0.13422
0.19562     0.12824
0.17033     0.12127
0.14645     0.11341
0.12408     0.10483
0.10332     0.09565
0.08427     0.08600
0.06699     0.07603
0.05156     0.06588
0.03806     0.05569
0.02653     0.04553
0.01704     0.03542
0.00961     0.02557
0.00428     0.01626
0.00107     0.00771
0.00000     0.00000
0.00107     -0.00729
0.00428     -0.01462
0.00961     -0.02219
0.01704     -0.02985
0.02653     -0.03711
0.03806     -0.04374
0.05156     -0.04971
0.06699     -0.05507
0.08427     -0.05985
0.10332     -0.06405
0.12408     -0.06770
0.14645     -0.07085
0.17033     -0.07354
0.19562     -0.07576
0.22221     -0.07750
0.25000     -0.07876
0.27886     -0.07953
0.30866     -0.07979
0.33928     -0.07955
0.37059     -0.07881
0.40245     -0.07760
0.43474     -0.07590
0.46730     -0.07370
0.50000     -0.07096
0.53270     -0.06771
0.56526     -0.06401
0.59755     -0.05992
0.62941     -0.05553
0.66072     -0.05093
0.69134     -0.04624
0.72114     -0.04156
0.75000     -0.03699
0.77779     -0.03258
0.80438     -0.02841
0.82967     -0.02453
0.85355     -0.02098
0.87592     -0.01777
0.89668     -0.01481
0.91573     -0.01202
0.93301     -0.00939
0.94844     -0.00698
0.96194     -0.00487
0.97347     -0.00311
0.98296     -0.00174
0.99039     -0.00085
0.99572     -0.00032
0.99893     -0.00030
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 84-W-218PreviewDetails
AH 93-W-215PreviewDetails
NACA 4424PreviewDetails
EPPLER 858 AIRFOILPreviewDetails
NACA 4421PreviewDetails
NACA 65(4)-421 a=0.5PreviewDetails
GOE 770 AIRFOILPreviewDetails
NACA 2424PreviewDetails
B-29 ROOT AIRFOILPreviewDetails
GOE 434 AIRFOILPreviewDetails

Polars for FX 83-W-227 (fx83w227-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx83w227-il50,00092.3 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx83w227-il50,00057 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx83w227-il100,00098.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx83w227-il100,000531.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx83w227-il200,000956.2 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx83w227-il200,000550 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   fx83w227-il500,000973.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx83w227-il500,000562.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx83w227-il1,000,000984.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx83w227-il1,000,000573.5 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit