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

EPPLER 543 AIRFOIL (e543-il)

EPPLER 543 AIRFOIL - Eppler E543 general aviation airfoil


Airfoil e543-il
Details Dat file Parser  
(e543-il) EPPLER 543 AIRFOIL
Eppler E543 general aviation airfoil
Max thickness 17.2% at 40.7% chord.
Max camber 1.9% at 31% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 543 AIRFOIL
       36.       37.

 0.0000100 -.0001800
 0.0000200 0.0005400
 0.0002200 0.0020700
 0.0006300 0.0037000
 0.0016200 0.0062900
 0.0029400 0.0088600
 0.0105800 0.0185600
 0.0227400 0.0288900
 0.0392600 0.0394000
 0.0600000 0.0497700
 0.0847700 0.0597500
 0.1133700 0.0691000
 0.1455300 0.0776500
 0.1809400 0.0852400
 0.2192600 0.0917200
 0.2601200 0.0969600
 0.3030800 0.1008400
 0.3477200 0.1032600
 0.3935300 0.1040400
 0.4401300 0.1029400
 0.4873500 0.0997600
 0.5351400 0.0945800
 0.5833300 0.0877800
 0.6314700 0.0797800
 0.6790600 0.0709200
 0.7256000 0.0615700
 0.7704901 0.0520800
 0.8131400 0.0428100
 0.8529000 0.0340600
 0.8891000 0.0261000
 0.9210600 0.0191000
 0.9481400 0.0131600
 0.9697400 0.0081800
 0.9857399 0.0039200
 0.9962000 0.0009800
 1.0000000 0.0000000

 0.0000100 -.0001800
 0.0000500 -.0008600
 0.0001800 -.0015000
 0.0004200 -.0021200
 0.0007500 -.0027500
 0.0011700 -.0033900
 0.0022200 -.0046800
 0.0035300 -.0060000
 0.0059600 -.0080300
 0.0138000 -.0129900
 0.0293700 -.0199700
 0.0500800 -.0268000
 0.0756500 -.0333700
 0.1057900 -.0395800
 0.1401400 -.0454100
 0.1782400 -.0508300
 0.2195900 -.0557500
 0.2636700 -.0600900
 0.3099200 -.0637200
 0.3578000 -.0665600
 0.4067300 -.0684800
 0.4561400 -.0693600
 0.5054400 -.0690600
 0.5540600 -.0674100
 0.6013700 -.0639800
 0.6474000 -.0581000
 0.6927201 -.0497400
 0.7379100 -.0396700
 0.7828400 -.0293200
 0.8264601 -.0199200
 0.8675900 -.0120900
 0.9049900 -.0062000
 0.9374700 -.0023100
 0.9639900 -.0002100
 0.9837101 0.0004600
 0.9958799 0.0002400
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 547 AIRFOILPreviewDetails
EPPLER 542 AIRFOILPreviewDetails
EPPLER 545 AIRFOILPreviewDetails
EPPLER 544 AIRFOILPreviewDetails
EPPLER 540 AIRFOILPreviewDetails
EPPLER 548 AIRFOILPreviewDetails
EPPLER 549 AIRFOILPreviewDetails
EPPLER 546 AIRFOILPreviewDetails
EPPLER 541 AIRFOILPreviewDetails
FX 61-163 AIRFOILPreviewDetails

Polars for EPPLER 543 AIRFOIL (e543-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e543-il50,000921.3 at α=12.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e543-il50,000517.9 at α=11.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e543-il100,000942.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   e543-il100,000535.3 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e543-il200,000956.6 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e543-il200,000558.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e543-il500,000986.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e543-il500,000582.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e543-il1,000,0009108.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e543-il1,000,000598.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit