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

GOE 419 AIRFOIL (goe419-il)

GOE 419 AIRFOIL - Gottingen 419 airfoil


Airfoil goe419-il
Details Dat file Parser  
(goe419-il) GOE 419 AIRFOIL
Gottingen 419 airfoil
Max thickness 5.3% at 30% chord.
Max camber 4.1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 419 AIRFOIL
       17.       17.

 0.0000000 0.0050000
 0.0125000 0.0135000
 0.0250000 0.0190000
 0.0500000 0.0295000
 0.0750000 0.0380000
 0.1000000 0.0445000
 0.1500000 0.0550000
 0.2000000 0.0625000
 0.3000000 0.0700000
 0.4000000 0.0705000
 0.5000000 0.0670000
 0.6000000 0.0590000
 0.7000000 0.0490000
 0.8000000 0.0350000
 0.9000000 0.0200000
 0.9500000 0.0120000
 1.0000000 0.0000000

 0.0000000 0.0050000
 0.0125000 0.0005000
 0.0250000 0.0000000
 0.0500000 0.0010000
 0.0750000 0.0030000
 0.1000000 0.0050000
 0.1500000 0.0090000
 0.2000000 0.0125000
 0.3000000 0.0170000
 0.4000000 0.0175000
 0.5000000 0.0155000
 0.6000000 0.0130000
 0.7000000 0.0095000
 0.8000000 0.0060000
 0.9000000 0.0030000
 0.9500000 0.0015000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 397 AIRFOILPreviewDetails
GOE 372 AIRFOILPreviewDetails
GOE 590 AIRFOILPreviewDetails
USA 5 AIRFOILPreviewDetails
GOE 377 AIRFOILPreviewDetails
Coanda 1PreviewDetails
GOE 142 (MVA H.19) AIRFOILPreviewDetails
GOE 210 (DAIMLER) AIRFOILPreviewDetails
NACA M16 AIRFOILPreviewDetails
USA 41 AIRFOILPreviewDetails

Polars for GOE 419 AIRFOIL (goe419-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe419-il50,000942.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe419-il50,000540.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe419-il100,000960 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe419-il100,000559 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe419-il200,000979.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe419-il200,000578.5 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe419-il500,0009109.2 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe419-il500,0005102 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   goe419-il1,000,0009125 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   goe419-il1,000,0005119.3 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit