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

EPPLER 421 AIRFOIL (e421-il)

EPPLER 421 AIRFOIL - Eppler E421 high lift airfoil


Airfoil e421-il
Details Dat file Parser  
(e421-il) EPPLER 421 AIRFOIL
Eppler E421 high lift airfoil
Max thickness 14.5% at 26% chord.
Max camber 8.6% at 37.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 421 AIRFOIL
       34.       39.

 0.0002600 0.0025000
 0.0024400 0.0144400
 0.0083500 0.0277900
 0.0180100 0.0420100
 0.0313900 0.0566500
 0.0484000 0.0713400
 0.0689400 0.0857400
 0.0928500 0.0995300
 0.1199200 0.1124400
 0.1499200 0.1241900
 0.1825500 0.1345200
 0.2175100 0.1431800
 0.2544300 0.1498200
 0.2931300 0.1540500
 0.3335100 0.1556500
 0.3755300 0.1544200
 0.4193300 0.1504600
 0.4648300 0.1442500
 0.5116000 0.1362300
 0.5591700 0.1267700
 0.6070200 0.1162100
 0.6545900 0.1049200
 0.7012800 0.0932200
 0.7464800 0.0814400
 0.7895401 0.0698500
 0.8298300 0.0586800
 0.8667300 0.0481000
 0.8996601 0.0382300
 0.9280500 0.0290200
 0.9517300 0.0201900
 0.9711300 0.0119400
 0.9863000 0.0052800
 0.9963900 0.0012600
 1.0000000 0.0000000

 0.0002600 0.0025000
 0.0003000 -.0003500
 0.0006600 -.0033400
 0.0011000 -.0051900
 0.0016900 -.0068800
 0.0020400 -.0076700
 0.0024500 -.0084100
 0.0029100 -.0090800
 0.0034600 -.0097000
 0.0041000 -.0102900
 0.0048300 -.0108700
 0.0064800 -.0119800
 0.0083900 -.0130300
 0.0117000 -.0145100
 0.0218500 -.0175800
 0.0401900 -.0202200
 0.0636800 -.0208700
 0.0922800 -.0193900
 0.1260800 -.0157100
 0.1652400 -.0099500
 0.2100300 -.0025800
 0.2602600 0.0053800
 0.3152000 0.0131000
 0.3740000 0.0198300
 0.4354000 0.0247700
 0.4977100 0.0277200
 0.5596700 0.0290800
 0.6204200 0.0291100
 0.6791500 0.0279000
 0.7349100 0.0254800
 0.7867300 0.0221500
 0.8338700 0.0183400
 0.8758100 0.0144000
 0.9121200 0.0106600
 0.9425400 0.0074200
 0.9669600 0.0047300
 0.9850399 0.0024600
 0.9962200 0.0007100
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

USA 32 AIRFOILPreviewDetails
USA 31 AIRFOILPreviewDetails
FX 73-CL3-152PreviewDetails
GOE 592 AIRFOILPreviewDetails
GOE 440 AIRFOILPreviewDetails
GOE 227 (MVA H.37) AIRFOILPreviewDetails
FX74_CL5_140PreviewDetails
EPPLER 422 AIRFOILPreviewDetails
GOE 234 (MVA CA5) AIRFOILPreviewDetails
GOE 226 (MVA H.36) AIRFOILPreviewDetails

Polars for EPPLER 421 AIRFOIL (e421-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e421-il50,00095.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e421-il50,000520 at α=0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e421-il100,000927.7 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   e421-il100,000548 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   e421-il200,000963 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e421-il200,000574.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e421-il500,0009107.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e421-il500,0005109.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e421-il1,000,0009141.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e421-il1,000,0005141.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit