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EPPLER 553 AIRFOIL (e553-il)

EPPLER 553 AIRFOIL - Eppler E553 general aviation airfoil


Airfoil e553-il
Details Dat file Parser  
(e553-il) EPPLER 553 AIRFOIL
Eppler E553 general aviation airfoil
Max thickness 18.1% at 31.8% chord.
Max camber 2.9% at 56.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 553 AIRFOIL
       35.       38.

 0.0000200 0.0005100
 0.0001800 0.0022800
 0.0005400 0.0041300
 0.0014600 0.0070600
 0.0052800 0.0143900
 0.0145500 0.0256500
 0.0281300 0.0373900
 0.0458500 0.0491900
 0.0675600 0.0607300
 0.0930400 0.0717200
 0.1220700 0.0819400
 0.1543700 0.0911400
 0.1896200 0.0991200
 0.2274800 0.1056300
 0.2676300 0.1104900
 0.3098400 0.1134300
 0.3538600 0.1143800
 0.3994900 0.1133200
 0.4464500 0.1104000
 0.4943700 0.1057700
 0.5428600 0.0996200
 0.5914900 0.0921800
 0.6398200 0.0837100
 0.6873500 0.0745000
 0.7335700 0.0648700
 0.7779200 0.0551400
 0.8198200 0.0456300
 0.8586700 0.0366100
 0.8938301 0.0283300
 0.9247100 0.0209500
 0.9507300 0.0145900
 0.9713400 0.0091500
 0.9865100 0.0044500
 0.9964000 0.0011400
 1.0000000 0.0000000

 0.0000200 0.0005100
 0.0000200 -.0003300
 0.0000900 -.0011400
 0.0002400 -.0019000
 0.0004900 -.0026400
 0.0008400 -.0034000
 0.0012600 -.0041600
 0.0023200 -.0057200
 0.0036300 -.0073000
 0.0060300 -.0097300
 0.0089000 -.0121800
 0.0219200 -.0204700
 0.0398800 -.0286800
 0.0624500 -.0365700
 0.0893400 -.0439600
 0.1201800 -.0507200
 0.1545400 -.0566900
 0.1919400 -.0616900
 0.2318900 -.0654600
 0.2738700 -.0676300
 0.3176500 -.0676700
 0.3633000 -.0653200
 0.4109000 -.0605600
 0.4606400 -.0537100
 0.5123800 -.0455600
 0.5655000 -.0368300
 0.6192800 -.0280800
 0.6729100 -.0198300
 0.7254699 -.0124800
 0.7760200 -.0063600
 0.8235700 -.0016900
 0.8671400 0.0014500
 0.9058000 0.0031100
 0.9386700 0.0034800
 0.9650400 0.0028900
 0.9843200 0.0017300
 0.9960600 0.0005300
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for EPPLER 553 AIRFOIL (e553-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e553-il50,00094.9 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e553-il50,000517.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e553-il100,000945.4 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e553-il100,000549.2 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e553-il200,000971.8 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e553-il200,000569.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e553-il500,000999.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e553-il500,000593.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   e553-il1,000,0009121.5 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e553-il1,000,0005111.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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