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

EPPLER 544 AIRFOIL (e544-il)

EPPLER 544 AIRFOIL - Eppler E544 general aviation airfoil


Airfoil e544-il
Details Dat file Parser  
(e544-il) EPPLER 544 AIRFOIL
Eppler E544 general aviation airfoil
Max thickness 17.5% at 40% chord.
Max camber 1.9% at 30.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 544 AIRFOIL
       36.       37.

 0.0000100 -.0001500
 0.0000200 0.0005900
 0.0002300 0.0021400
 0.0006500 0.0038000
 0.0016500 0.0064300
 0.0032500 0.0094800
 0.0111500 0.0193600
 0.0235600 0.0298300
 0.0403100 0.0404700
 0.0612700 0.0509500
 0.0862400 0.0610200
 0.1150200 0.0704600
 0.1473300 0.0790800
 0.1828600 0.0867200
 0.2212900 0.0932300
 0.2622100 0.0984900
 0.3052300 0.1023700
 0.3498800 0.1047800
 0.3956800 0.1055400
 0.4422400 0.1044000
 0.4893900 0.1011700
 0.5371000 0.0959100
 0.5851800 0.0890400
 0.6331800 0.0809500
 0.6806300 0.0719900
 0.7270000 0.0625300
 0.7717200 0.0529300
 0.8141900 0.0435300
 0.8537600 0.0346600
 0.8897800 0.0265700
 0.9215700 0.0194400
 0.9485100 0.0133900
 0.9699700 0.0083100
 0.9858600 0.0039800
 0.9962300 0.0010000
 1.0000000 0.0000000

 0.0000100 -.0001500
 0.0000500 -.0008500
 0.0001700 -.0015100
 0.0004100 -.0021400
 0.0007400 -.0027800
 0.0011500 -.0034400
 0.0021900 -.0047700
 0.0035000 -.0061300
 0.0059100 -.0082100
 0.0131100 -.0129900
 0.0283200 -.0201900
 0.0486400 -.0272600
 0.0737800 -.0340800
 0.1034600 -.0405300
 0.1373000 -.0465700
 0.1748700 -.0521600
 0.2156500 -.0572100
 0.2591200 -.0615900
 0.3047600 -.0652100
 0.3520100 -.0679300
 0.4003000 -.0696100
 0.4490700 -.0701000
 0.4977100 -.0692100
 0.5456300 -.0665000
 0.5928200 -.0613200
 0.6397700 -.0536200
 0.6869700 -.0440300
 0.7343600 -.0338700
 0.7809900 -.0242700
 0.8257800 -.0158800
 0.8676000 -.0091400
 0.9053200 -.0042500
 0.9378501 -.0011700
 0.9642800 -.0003500
 0.9838500 0.0006700
 0.9959200 0.0002900
 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 547 AIRFOILPreviewDetails
EPPLER 545 AIRFOILPreviewDetails
EPPLER 543 AIRFOILPreviewDetails
EPPLER 542 AIRFOILPreviewDetails
EPPLER 549 AIRFOILPreviewDetails
EPPLER 548 AIRFOILPreviewDetails
EPPLER 550 AIRFOILPreviewDetails
EPPLER 540 AIRFOILPreviewDetails
NACA 63(3)-218PreviewDetails
EPPLER 546 AIRFOILPreviewDetails

Polars for EPPLER 544 AIRFOIL (e544-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e544-il50,000921.5 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e544-il50,000518.5 at α=11.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e544-il100,000940.1 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e544-il100,000537.4 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e544-il200,000960.8 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e544-il200,000561.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e544-il500,000991 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e544-il500,000586.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   e544-il1,000,0009113.5 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e544-il1,000,0005101.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit