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

EPPLER 502 AIRFOIL (e502-il)

EPPLER 502 AIRFOIL - Eppler E502 general purpose airfoil


Airfoil e502-il
Details Dat file Parser  
(e502-il) EPPLER 502 AIRFOIL
Eppler E502 general purpose airfoil
Max thickness 15.6% at 42.1% chord.
Max camber 1.5% at 32.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 502 AIRFOIL
       36.       37.

 0.0000100 0.0001100
 0.0000600 0.0007400
 0.0001800 0.0014000
 0.0006000 0.0027900
 0.0012400 0.0042700
 0.0025800 0.0066100
 0.0075100 0.0126000
 0.0184300 0.0215900
 0.0339000 0.0308800
 0.0537500 0.0401800
 0.0778000 0.0492100
 0.1058400 0.0577800
 0.1375800 0.0657300
 0.1727200 0.0729000
 0.2109100 0.0791500
 0.2517600 0.0843800
 0.2948400 0.0884700
 0.3396900 0.0913400
 0.3858400 0.0928700
 0.4327800 0.0929600
 0.4799700 0.0913900
 0.5271200 0.0878700
 0.5741400 0.0822700
 0.6210100 0.0746100
 0.6679300 0.0653500
 0.7146299 0.0554100
 0.7603500 0.0455200
 0.8042600 0.0361800
 0.8455100 0.0277600
 0.8832300 0.0204500
 0.9166300 0.0143600
 0.9449500 0.0093800
 0.9677900 0.0052600
 0.9850500 0.0021400
 0.9961300 0.0004500
 1.0000000 0.0000000

 0.0000100 0.0001100
 0.0000300 -.0004800
 0.0001600 -.0010700
 0.0003800 -.0016600
 0.0006700 -.0022800
 0.0014600 -.0035300
 0.0024800 -.0048200
 0.0044400 -.0068000
 0.0067400 -.0087100
 0.0182600 -.0152500
 0.0351500 -.0216000
 0.0571800 -.0277800
 0.0839900 -.0337300
 0.1152200 -.0393600
 0.1505000 -.0445700
 0.1894100 -.0493000
 0.2315000 -.0534600
 0.2762900 -.0570100
 0.3232900 -.0598900
 0.3718900 -.0621100
 0.4214700 -.0635600
 0.4714100 -.0640900
 0.5211800 -.0635300
 0.5702100 -.0617500
 0.6179300 -.0583800
 0.6643800 -.0528000
 0.7102900 -.0453000
 0.7555900 -.0370700
 0.7994800 -.0289800
 0.8410800 -.0215800
 0.8794600 -.0151900
 0.9137500 -.0100100
 0.9430900 -.0060200
 0.9669001 -.0030200
 0.9847900 -.0010400
 0.9961000 -.0001600
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NLF(1)-0115PreviewDetails
EPPLER 546 AIRFOILPreviewDetails
AS5045 (15%)PreviewDetails
S8036 (16%)PreviewDetails
NACA 747A315PreviewDetails
EPPLER 541 AIRFOILPreviewDetails
EPPLER 542 AIRFOILPreviewDetails
EPPLER 540 AIRFOILPreviewDetails
GEMINI (smoothed)PreviewDetails
NACA 5-H-15 AIRFOILPreviewDetails

Polars for EPPLER 502 AIRFOIL (e502-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e502-il50,000924.6 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   e502-il50,000521 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e502-il100,000945.6 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   e502-il100,000536.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e502-il200,000958.8 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   e502-il200,000558 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   e502-il500,000988 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e502-il500,000580 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e502-il1,000,0009106.7 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e502-il1,000,000590.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit