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

E591 (e591-il)

E591 - Eppler E591 airfoil


Airfoil e591-il
Details Dat file Parser  
(e591-il) E591
Eppler E591 airfoil
Max thickness 15.7% at 25% chord.
Max camber 6% at 52.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
E591
1.0000 0.0000
.99670 .00151
.98763 .00596
.97400 .01261
.95603 .02021
.93329 .02833
.90580 .03709
.87400 .04649
.83835 .05635
.79931 .06650
.75738 .07674
.71308 .08683
.66693 .09655
.61945 .10567
.57115 .11396
.52254 .12120
.47411 .12720
.42634 .13177
.37968 .13476
.33458 .13601
.29138 .13535
.25036 .13275
.21180 .12821
.17596 .12177
.14305 .11353
.11326 .10364
.08675 .09230
.06364 .07972
.04403 .06620
.02798 .05207
.01550 .03772
.00666 .02364
.00149 .01035
.00004 -.00146
.00255 -.01054
.01087 -.01687
.02578 -.02178
.04618 -.02567
.07166 -.02847
.10182 -.03016
.13624 -.03061
.17460 -.02955
.21678 -.02692
.26259 -.02276
.31189 -.01726
.36440 -.01086
.41959 -.00404
.47679 .00277
.53527 .00917
.59420 .01477
.65267 .01924
.70971 .02232
.76431 .02384
.81546 .02372
.86213 .02201
.90338 .01888
.93829 .01454
.96583 .00941
.98516 .00454
.99636 .00118
1.0000 0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 502 AIRFOILPreviewDetails
GOE 535 AIRFOILPreviewDetails
GOE 498 AIRFOILPreviewDetails
EPPLER 560 AIRFOILPreviewDetails
St. CYR 234 (Bartel 17-IC)PreviewDetails
FX 73-CL2-152PreviewDetails
GOE 567 AIRFOILPreviewDetails
FX 76-MP-160PreviewDetails
MH 112 AirfoilPreviewDetails
MH 113 14.62%PreviewDetails

Polars for E591 (e591-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e591-il50,000910 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e591-il50,000534.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e591-il100,000952.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   e591-il100,000557.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e591-il200,000977.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e591-il200,000576.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e591-il500,0009107.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   e591-il500,000599.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e591-il1,000,0009129.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   e591-il1,000,0005118.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit