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

FX 79-W-660A (fx79w660a-il)

FX 79-W-660A - Wortman FX 79-W-660A airfoil for use on wind turbines (W)


Airfoil fx79w660a-il
Details Dat file Parser  
(fx79w660a-il) FX 79-W-660A
Wortman FX 79-W-660A airfoil for use on wind turbines (W)
Max thickness 66.4% at 46.7% chord.
Max camber 2.3% at 17% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 79-W-660A
1.00000     0.04237
0.99893     0.04675
0.99572     0.06511
0.99039     0.09568
0.98296     0.12165
0.97347     0.14515
0.96194     0.17177
0.94844     0.19916
0.93301     0.21790
0.91573     0.22514
0.89668     0.22957
0.87592     0.23485
0.85355     0.24217
0.82967     0.24998
0.80438     0.25807
0.77779     0.26657
0.75000     0.27539
0.72114     0.28458
0.69134     0.29485
0.66072     0.30538
0.62941     0.31564
0.59755     0.32466
0.56526     0.33181
0.53270     0.33761
0.50000     0.34205
0.46730     0.34493
0.43474     0.34602
0.40245     0.34523
0.37059     0.34304
0.33928     0.33961
0.30866     0.33477
0.27886     0.32755
0.25000     0.31788
0.22221     0.30577
0.19562     0.29192
0.17033     0.27629
0.14645     0.25910
0.12408     0.24036
0.10332     0.21986
0.08427     0.19848
0.06699     0.17666
0.05156     0.15456
0.03806     0.13260
0.02653     0.11013
0.01704     0.08589
0.00961     0.06302
0.00428     0.04013
0.00107     0.01289
0.00000     0.00000
0.00107     -0.01000
0.00428     -0.03159
0.00961     -0.05009
0.01704     -0.06748
0.02653     -0.08618
0.03806     -0.10393
0.05156     -0.12204
0.06699     -0.14043
0.08427     -0.15887
0.10332     -0.17731
0.12408     -0.19569
0.14645     -0.21322
0.17033     -0.22993
0.19562     -0.24564
0.22221     -0.25991
0.25000     -0.27268
0.27886     -0.28392
0.30866     -0.29376
0.33928     -0.30217
0.37059     -0.30912
0.40245     -0.31451
0.43474     -0.31785
0.46730     -0.31896
0.50000     -0.31820
0.53270     -0.31557
0.56526     -0.31106
0.59755     -0.30462
0.62941     -0.29682
0.66072     -0.28818
0.69134     -0.27823
0.72114     -0.26811
0.75000     -0.25870
0.77779     -0.24986
0.80438     -0.24186
0.82967     -0.23502
0.85355     -0.22902
0.87592     -0.22355
0.89668     -0.21856
0.91573     -0.21400
0.93301     -0.21023
0.94844     -0.20311
0.96194     -0.18023
0.97347     -0.14850
0.98296     -0.11916
0.99039     -0.08946
0.99572     -0.06296
0.99893     -0.04728
1.00000     -0.04239
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

AH 93-W-480BPreviewDetails
FX 79-W-470APreviewDetails
EPPLER 864 STRUT AIRFOILPreviewDetails
EPPLER 863 STRUT AIRFOILPreviewDetails
WORTMANN FX 77-W-343 AIRFOILPreviewDetails
GOE 570 AIRFOILPreviewDetails
EPPLER 862 STRUT AIRFOILPreviewDetails
Griffith 30% Suction AirfoilPreviewDetails
HAM-STD HS1-430 AIRFOILPreviewDetails
AH 93-W-300PreviewDetails

Polars for FX 79-W-660A (fx79w660a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx79w660a-il50,00090.8 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx79w660a-il50,00053 at α=-10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx79w660a-il100,00095.2 at α=-10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx79w660a-il100,00055.5 at α=-5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx79w660a-il200,00098.7 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx79w660a-il200,00056 at α=-2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx79w660a-il500,00095 at α=13.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx79w660a-il500,00054.7 at α=15.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx79w660a-il1,000,00096.5 at α=16.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx79w660a-il1,000,00055.4 at α=15.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit