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

EPPLER 1213 AIRFOIL (e1213-il)

EPPLER 1213 AIRFOIL - Eppler E1213 general aviation airfoil


Airfoil e1213-il
Details Dat file Parser  
(e1213-il) EPPLER 1213 AIRFOIL
Eppler E1213 general aviation airfoil
Max thickness 17.4% at 22.1% chord.
Max camber 2.1% at 35.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
EPPLER 1213 AIRFOIL
      31.0      30.0
 
 0.0000000 0.0000000
 0.0071778 0.0222617
 0.0168026 0.0356786
 0.0302375 0.0490043
 0.0473222 0.0618287
 0.0678967 0.0737419
 0.0917408 0.0842139
 0.1189343 0.0927247
 0.1496971 0.0991342
 0.1838793 0.1035026
 0.2212908 0.1057598
 0.2617716 0.1059259
 0.3050619 0.1041009
 0.3508815 0.1004251
 0.3988906 0.0950885
 0.4486893 0.0883613
 0.4998277 0.0805235
 0.5517857 0.0719155
 0.6039737 0.0628774
 0.6557416 0.0537494
 0.7063895 0.0448618
 0.7551976 0.0364749
 0.8013760 0.0288388
 0.8441945 0.0221140
 0.8829133 0.0163606
 0.9168423 0.0115988
 0.9453616 0.0076689
 0.9682009 0.0043410
 0.9853203 0.0017651
 0.9962201 0.0003713
 1.0000000 0.0000000
 
 0.0000000 0.0000000
 0.0042956 -.0132080
 0.0141422 -.0236516
 0.0285489 -.0340068
 0.0470659 -.0437433
 0.0694834 -.0524112
 0.0956314 -.0595904
 0.1254502 -.0649107
 0.1589098 -.0680923
 0.1961502 -.0689151
 0.2374615 -.0675893
 0.2826834 -.0647947
 0.3311757 -.0610113
 0.3822782 -.0564888
 0.4353310 -.0514869
 0.4896139 -.0461855
 0.5444168 -.0407742
 0.5990198 -.0353929
 0.6526927 -.0301612
 0.7047154 -.0252090
 0.7544080 -.0206160
 0.8010703 -.0164520
 0.8440725 -.0127567
 0.8828144 -.0095599
 0.9167160 -.0068415
 0.9452873 -.0045513
 0.9682185 -.0025391
 0.9853793 -.0009750
 0.9962399 -.0001787
 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 E1212MOD AIRFOILPreviewDetails
MH 102 16.99%PreviewDetails
EPPLER E1212 AIRFOILPreviewDetails
NACA 2418PreviewDetails
NASA/LANGLEY LS(1)-0417MOD AIRFOILPreviewDetails
NASA/LANGLEY NLF(1)-0416 AIRFOILPreviewDetails
EPPLER 550 AIRFOILPreviewDetails
DAVIS BASIC B-24 WING AIRFOILPreviewDetails
CLARK YM-18 AIRFOILPreviewDetails
EPPLER 548 AIRFOILPreviewDetails

Polars for EPPLER 1213 AIRFOIL (e1213-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e1213-il50,000911.5 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e1213-il50,000522.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e1213-il100,000930.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e1213-il100,000539.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e1213-il200,000951.7 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e1213-il200,000555.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e1213-il500,000979.4 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   e1213-il500,000580.2 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e1213-il1,000,0009102.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   e1213-il1,000,0005101.1 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit