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

EPPLER 546 AIRFOIL (e546-il)

EPPLER 546 AIRFOIL - Eppler E546 general aviation airfoil


Airfoil e546-il
Details Dat file Parser  
(e546-il) EPPLER 546 AIRFOIL
Eppler E546 general aviation airfoil
Max thickness 16.2% at 40.3% chord.
Max camber 1.8% at 26.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 546 AIRFOIL
       36.       37.

 0.0000100 -.0001600
 0.0000200 0.0005500
 0.0002200 0.0020500
 0.0006300 0.0036400
 0.0016100 0.0061800
 0.0028500 0.0085900
 0.0103600 0.0180800
 0.0223400 0.0281800
 0.0386400 0.0384400
 0.0591300 0.0485500
 0.0836100 0.0582300
 0.1118800 0.0672500
 0.1436800 0.0754400
 0.1787100 0.0826200
 0.2166300 0.0886200
 0.2570500 0.0933100
 0.2995600 0.0964800
 0.3438500 0.0979000
 0.3896800 0.0974500
 0.4368900 0.0951500
 0.4852000 0.0912100
 0.5342000 0.0858500
 0.5834600 0.0793100
 0.6324900 0.0718400
 0.6807900 0.0637400
 0.7278100 0.0552900
 0.7729800 0.0468000
 0.8156900 0.0385500
 0.8553100 0.0307900
 0.8912100 0.0237300
 0.9227600 0.0175000
 0.9493800 0.0121800
 0.9705300 0.0076400
 0.9861400 0.0036900
 0.9963100 0.0009300
 1.0000000 0.0000000

 0.0000100 -.0001600
 0.0000500 -.0008300
 0.0001800 -.0014600
 0.0004100 -.0020700
 0.0007400 -.0026800
 0.0011500 -.0033100
 0.0021800 -.0045800
 0.0034800 -.0058700
 0.0058700 -.0078600
 0.0138000 -.0128100
 0.0292500 -.0196500
 0.0498000 -.0263300
 0.0751600 -.0327300
 0.1050400 -.0387700
 0.1390900 -.0444000
 0.1768600 -.0496000
 0.2178400 -.0542800
 0.2615300 -.0583300
 0.3073700 -.0616600
 0.3548100 -.0641300
 0.4033000 -.0656200
 0.4522500 -.0659800
 0.5010900 -.0650300
 0.5491900 -.0623300
 0.5965800 -.0572300
 0.6438100 -.0497400
 0.6912600 -.0406800
 0.7386200 -.0312400
 0.7849700 -.0223800
 0.8292800 -.0146600
 0.8704799 -.0084800
 0.9075000 -.0039900
 0.9393400 -.0011600
 0.9651500 0.0002600
 0.9842500 0.0005900
 0.9960200 0.0002600
 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 542 AIRFOILPreviewDetails
EPPLER 502 AIRFOILPreviewDetails
EPPLER 543 AIRFOILPreviewDetails
FX 61-163 AIRFOILPreviewDetails
EPPLER 545 AIRFOILPreviewDetails
EPPLER 547 AIRFOILPreviewDetails
KC-135 BL52.44 AIRFOILPreviewDetails
NLF(1)-0115PreviewDetails
EPPLER 541 AIRFOILPreviewDetails
EPPLER 544 AIRFOILPreviewDetails

Polars for EPPLER 546 AIRFOIL (e546-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e546-il50,00098.9 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e546-il50,000521.6 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e546-il100,000944.8 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e546-il100,000543.3 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e546-il200,000961.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e546-il200,000561.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e546-il500,000987.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e546-il500,000582.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e546-il1,000,0009106.6 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e546-il1,000,000596.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit