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

EPPLER 593 AIRFOIL (e593-il)

EPPLER 593 AIRFOIL - Eppler E593 airfoil


Airfoil e593-il
Details Dat file Parser  
(e593-il) EPPLER 593 AIRFOIL
Eppler E593 airfoil
Max thickness 11.3% at 24.2% chord.
Max camber 4.6% at 29.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 593 AIRFOIL
       34.       38.

 0.0000100 0.0000400
 0.0001000 0.0015800
 0.0006000 0.0042700
 0.0048100 0.0135000
 0.0130200 0.0237800
 0.0251500 0.0345500
 0.0411200 0.0454200
 0.0608200 0.0560600
 0.0840800 0.0662100
 0.1107200 0.0755900
 0.1404700 0.0839800
 0.1730600 0.0911500
 0.2081400 0.0968700
 0.2453500 0.1008900
 0.2842800 0.1028000
 0.3248300 0.1020700
 0.3671500 0.0983700
 0.4116900 0.0916000
 0.4590700 0.0824400
 0.5090400 0.0722500
 0.5606100 0.0619200
 0.6128000 0.0519100
 0.6646600 0.0425500
 0.7152800 0.0340600
 0.7638100 0.0265800
 0.8094200 0.0201600
 0.8513700 0.0148200
 0.8890000 0.0104800
 0.9217100 0.0070300
 0.9490899 0.0043000
 0.9709200 0.0022200
 0.9869200 0.0008400
 0.9967000 0.0001700
 1.0000000 0.0000000

 0.0000100 0.0000400
 0.0000900 -.0013800
 0.0002000 -.0020500
 0.0003700 -.0026800
 0.0006000 -.0032500
 0.0009200 -.0038000
 0.0013300 -.0043300
 0.0018100 -.0048600
 0.0029800 -.0059200
 0.0043800 -.0069600
 0.0069000 -.0085000
 0.0182200 -.0129400
 0.0348400 -.0163100
 0.0566000 -.0182300
 0.0836300 -.0186900
 0.1160000 -.0178900
 0.1535400 -.0163000
 0.1957500 -.0142600
 0.2420800 -.0120200
 0.2919600 -.0098700
 0.3445900 -.0081000
 0.3989900 -.0067800
 0.4543700 -.0057500
 0.5100700 -.0049000
 0.5646100 -.0042000
 0.6198800 -.0036200
 0.6727101 -.0031400
 0.7233300 -.0027500
 0.7711700 -.0024200
 0.8156500 -.0021500
 0.8562600 -.0019000
 0.8925200 -.0016600
 0.9239900 -.0013600
 0.9503900 -.0009400
 0.9715300 -.0004600
 0.9871100 -.0001100
 0.9967400 0.0000000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 598 AIRFOILPreviewDetails
LISSAMAN 7769 AIRFOILPreviewDetails
GOE 321 (HANSA-BRANDENBURG III.1)PreviewDetails
GOE 323 (HANSA-BRANDENBURG V.1)PreviewDetails
SPICA 11.73% smoothedPreviewDetails
GOE 436 AIRFOILPreviewDetails
NACA M18 AIRFOILPreviewDetails
NACA M18PreviewDetails
FX 77-W-121PreviewDetails
EPPLER 334 AIRFOILPreviewDetails

Polars for EPPLER 593 AIRFOIL (e593-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e593-il50,00097.3 at α=-0.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e593-il50,000516.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e593-il100,000925 at α=13.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e593-il100,000536.3 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   e593-il200,000971.4 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   e593-il200,000574.2 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   e593-il500,0009115.2 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e593-il500,0005113.5 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e593-il1,000,0009148.1 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e593-il1,000,0005140.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit