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EPPLER 541 AIRFOIL (e541-il)

EPPLER 541 AIRFOIL - Eppler E541 general aviation airfoil


Airfoil e541-il
Details Dat file Parser  
(e541-il) EPPLER 541 AIRFOIL
Eppler E541 general aviation airfoil
Max thickness 16.6% at 46.2% chord.
Max camber 1.7% at 36.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 541 AIRFOIL
       36.       37.

 0.0000100 0.0002200
 0.0000600 0.0008800
 0.0003400 0.0022800
 0.0008400 0.0037800
 0.0019500 0.0061600
 0.0026300 0.0073500
 0.0101600 0.0161400
 0.0223600 0.0255900
 0.0390700 0.0352600
 0.0601500 0.0448600
 0.0853900 0.0541500
 0.1145800 0.0629300
 0.1474500 0.0710300
 0.1836700 0.0783200
 0.2229000 0.0846700
 0.2647400 0.0899900
 0.3087600 0.0941800
 0.3545000 0.0971700
 0.4014800 0.0989100
 0.4491600 0.0993200
 0.4970400 0.0983200
 0.5445500 0.0957400
 0.5913200 0.0913200
 0.6372400 0.0848400
 0.6825100 0.0764400
 0.7270700 0.0668000
 0.7704300 0.0566100
 0.8120100 0.0463600
 0.8511500 0.0365300
 0.8871700 0.0275300
 0.9193100 0.0196600
 0.9468200 0.0131100
 0.9689800 0.0078300
 0.9854800 0.0036100
 0.9961700 0.0008800
 1.0000000 0.0000000

 0.0000100 0.0002200
 0.0000100 -.0004100
 0.0001100 -.0009900
 0.0003100 -.0015500
 0.0006100 -.0021300
 0.0009900 -.0027100
 0.0019600 -.0039100
 0.0032000 -.0051400
 0.0055100 -.0070300
 0.0148700 -.0126100
 0.0308000 -.0192100
 0.0518500 -.0256700
 0.0777700 -.0318800
 0.1082800 -.0377700
 0.1430200 -.0433200
 0.1815300 -.0485000
 0.2233100 -.0532500
 0.2678200 -.0574800
 0.3145300 -.0610900
 0.3628700 -.0639900
 0.4122700 -.0660700
 0.4621500 -.0672400
 0.5119400 -.0673900
 0.5610400 -.0663700
 0.6088900 -.0640300
 0.6548600 -.0599400
 0.6990300 -.0533900
 0.7421200 -.0443900
 0.7847800 -.0338300
 0.8268800 -.0233900
 0.8672000 -.0143700
 0.9043600 -.0073900
 0.9370000 -.0027300
 0.9638301 0.0002600
 0.9837200 0.0004600
 0.9959100 0.0002400
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for EPPLER 541 AIRFOIL (e541-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e541-il50,000925.2 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e541-il50,000521 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e541-il100,000940.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e541-il100,000529.3 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   e541-il200,000946.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e541-il200,000550.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e541-il500,000978.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e541-il500,000579.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   e541-il1,000,0009106.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e541-il1,000,000596.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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