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EPPLER 554 AIRFOIL (e554-il)

EPPLER 554 AIRFOIL - Eppler E554 general aviation airfoil


Airfoil e554-il
Details Dat file Parser  
(e554-il) EPPLER 554 AIRFOIL
Eppler E554 general aviation airfoil
Max thickness 18.2% at 31.8% chord.
Max camber 2.7% at 56.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 554 AIRFOIL
       35.       38.

 0.0000100 0.0003400
 0.0001100 0.0021400
 0.0004300 0.0040400
 0.0012600 0.0070300
 0.0051500 0.0150400
 0.0142200 0.0266100
 0.0275100 0.0386700
 0.0448600 0.0507800
 0.0661100 0.0626200
 0.0910500 0.0738800
 0.1194400 0.0843100
 0.1510200 0.0936500
 0.1854600 0.1016800
 0.2224300 0.1081400
 0.2616000 0.1127300
 0.3027200 0.1151800
 0.3456500 0.1151800
 0.3905600 0.1126700
 0.4374100 0.1081000
 0.4857700 0.1019100
 0.5351500 0.0944400
 0.5850200 0.0860200
 0.6347900 0.0769900
 0.6838500 0.0676700
 0.7315200 0.0583400
 0.7771400 0.0492800
 0.8200400 0.0407000
 0.8595300 0.0327500
 0.8950200 0.0255600
 0.9259101 0.0191800
 0.9517100 0.0136100
 0.9719800 0.0087300
 0.9868200 0.0043300
 0.9964800 0.0011200
 1.0000000 0.0000000

 0.0000100 0.0003400
 0.0000300 -.0005200
 0.0001300 -.0013400
 0.0003000 -.0021200
 0.0005700 -.0028800
 0.0009400 -.0036400
 0.0013800 -.0044200
 0.0024800 -.0060000
 0.0038400 -.0076000
 0.0063000 -.0100400
 0.0087700 -.0121400
 0.0217900 -.0204400
 0.0397600 -.0286400
 0.0623600 -.0365000
 0.0892700 -.0438400
 0.1201400 -.0505400
 0.1545200 -.0564500
 0.1919500 -.0613700
 0.2319300 -.0650700
 0.2739300 -.0671700
 0.3177300 -.0671700
 0.3634000 -.0647100
 0.4110100 -.0598800
 0.4607600 -.0529700
 0.5125200 -.0447600
 0.5656600 -.0359800
 0.6194600 -.0272000
 0.6731000 -.0189200
 0.7256900 -.0115700
 0.7762600 -.0054700
 0.8238400 -.0008400
 0.8674300 0.0022200
 0.9061100 0.0037800
 0.9390000 0.0040000
 0.9653500 0.0032100
 0.9845200 0.0018600
 0.9961200 0.0005600
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for EPPLER 554 AIRFOIL (e554-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e554-il50,00094.8 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e554-il50,000518.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   e554-il100,000936.4 at α=12.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e554-il100,000546.2 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   e554-il200,000969 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e554-il200,000570.2 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e554-il500,0009103.2 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e554-il500,000598.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e554-il1,000,0009127.8 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e554-il1,000,0005118.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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