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EPPLER 561 AIRFOIL (e561-il)

EPPLER 561 AIRFOIL - Eppler E561 general aviation airfoil


Airfoil e561-il
Details Dat file Parser  
(e561-il) EPPLER 561 AIRFOIL
Eppler E561 general aviation airfoil
Max thickness 16.9% at 27.9% chord.
Max camber 5.1% at 45.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 561 AIRFOIL
       33.       29.

 0.0000200 0.0009200
 0.0033000 0.0121300
 0.0107700 0.0247100
 0.0222400 0.0379600
 0.0376300 0.0514400
 0.0567800 0.0647800
 0.0795300 0.0776300
 0.1056600 0.0896900
 0.1349300 0.1006400
 0.1671300 0.1101700
 0.2020400 0.1180000
 0.2394400 0.1239000
 0.2791500 0.1276700
 0.3210000 0.1291800
 0.3649200 0.1284400
 0.4106900 0.1256800
 0.4579300 0.1211700
 0.5061900 0.1151100
 0.5550300 0.1077600
 0.6039200 0.0993800
 0.6523400 0.0902400
 0.6997100 0.0806100
 0.7454600 0.0707600
 0.7889900 0.0609400
 0.8297000 0.0513700
 0.8670099 0.0422300
 0.9003700 0.0336500
 0.9292800 0.0257400
 0.9532400 0.0184300
 0.9722300 0.0114900
 0.9867401 0.0053700
 0.9964600 0.0013300
 1.0000000 0.0000000

 0.0000200 0.0009200
 0.0022700 -.0082700
 0.0106700 -.0164100
 0.0242600 -.0243700
 0.0424700 -.0316800
 0.0650100 -.0379700
 0.0916800 -.0429000
 0.1223300 -.0462300
 0.1568300 -.0477300
 0.1951200 -.0473300
 0.2370600 -.0450400
 0.2825000 -.0409900
 0.3312700 -.0353800
 0.3832000 -.0286400
 0.4378200 -.0214600
 0.4942900 -.0143700
 0.5517400 -.0077500
 0.6092600 -.0018700
 0.6659600 0.0030400
 0.7209100 0.0068500
 0.7732200 0.0094400
 0.8219900 0.0108100
 0.8663900 0.0109800
 0.9056200 0.0100500
 0.9389300 0.0081700
 0.9655200 0.0055900
 0.9847000 0.0028800
 0.9961900 0.0007900
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for EPPLER 561 AIRFOIL (e561-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e561-il50,00095.6 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e561-il50,000526.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e561-il100,000939.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e561-il100,000552.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e561-il200,000970 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e561-il200,000574.1 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e561-il500,0009105 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e561-il500,0005104.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   e561-il1,000,0009134.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e561-il1,000,0005128.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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