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

FX 84-W-140 (fx84w140-il)

FX 84-W-140 - Wortmann FX 84-W-140 airfoil for use on wind turbines (W)


Airfoil fx84w140-il
Details Dat file Parser  
(fx84w140-il) FX 84-W-140
Wortmann FX 84-W-140 airfoil for use on wind turbines (W)
Max thickness 14.1% at 37.1% chord.
Max camber 4.2% at 40.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 84-W-140
1.00000     0.00000
0.99893     0.00014
0.99572     0.00060
0.99039     0.00146
0.98296     0.00278
0.97347     0.00461
0.96194     0.00701
0.94844     0.01001
0.93301     0.01362
0.91573     0.01784
0.89668     0.02264
0.87592     0.02801
0.85355     0.03386
0.82967     0.04015
0.80438     0.04677
0.77779     0.05360
0.75000     0.06057
0.72114     0.06753
0.69134     0.07436
0.66072     0.08095
0.62941     0.08715
0.59755     0.09286
0.56526     0.09801
0.53270     0.10244
0.50000     0.10612
0.46730     0.10898
0.43474     0.11092
0.40245     0.11198
0.37059     0.11210
0.33928     0.11127
0.30866     0.10955
0.27886     0.10690
0.25000     0.10342
0.22221     0.09918
0.19562     0.09421
0.17033     0.08867
0.14645     0.08258
0.12408     0.07601
0.10332     0.06905
0.08427     0.06179
0.06699     0.05439
0.05156     0.04693
0.03806     0.03950
0.02653     0.03220
0.01704     0.02510
0.00961     0.01832
0.00428     0.01180
0.00107     0.00564
0.00000     0.00000
0.00107     -0.00509
0.00428     -0.00961
0.00961     -0.01369
0.01704     -0.01734
0.02653     -0.02047
0.03806     -0.02313
0.05156     -0.02534
0.06699     -0.02714
0.08427     -0.02856
0.10332     -0.02964
0.12408     -0.03042
0.14645     -0.03094
0.17033     -0.03122
0.19562     -0.03130
0.22221     -0.03121
0.25000     -0.03097
0.27886     -0.03060
0.30866     -0.03010
0.33928     -0.02948
0.37059     -0.02872
0.40245     -0.02784
0.43474     -0.02682
0.46730     -0.02565
0.50000     -0.02433
0.53270     -0.02286
0.56526     -0.02124
0.59755     -0.01948
0.62941     -0.01759
0.66072     -0.01561
0.69134     -0.01356
0.72114     -0.01148
0.75000     -0.00942
0.77779     -0.00742
0.80438     -0.00555
0.82967     -0.00383
0.85355     -0.00231
0.87592     -0.00103
0.89668     -0.00001
0.91573     0.00073
0.93301     0.00122
0.94844     0.00147
0.96194     0.00149
0.97347     0.00133
0.98296     0.00104
0.99039     0.00069
0.99572     0.00034
0.99893     0.00010
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 585 AIRFOILPreviewDetails
EPPLER 582 AIRFOILPreviewDetails
AH 93-W-145PreviewDetails
NACA 2-H-15 AIRFOILPreviewDetails
EPPLER 668 AIRFOILPreviewDetails
EPPLER 434 AIRFOILPreviewDetails
EPPLER 433 AIRFOILPreviewDetails
AH 81-K-144/17PreviewDetails
FX 84-W-150PreviewDetails
NASA/LANGLEY NLF(1)-0215F AIRFOILPreviewDetails

Polars for FX 84-W-140 (fx84w140-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx84w140-il50,00095.9 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx84w140-il50,000517.2 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx84w140-il100,000946.3 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx84w140-il100,000550.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx84w140-il200,000979.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx84w140-il200,000579.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx84w140-il500,0009118.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx84w140-il500,0005113.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx84w140-il1,000,0009147.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx84w140-il1,000,0005136.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit