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

GOE 427 AIRFOIL (goe427-il)

GOE 427 AIRFOIL - Gottingen 427 airfoil


Airfoil goe427-il
Details Dat file Parser  
(goe427-il) GOE 427 AIRFOIL
Gottingen 427 airfoil
Max thickness 4.6% at 20% chord.
Max camber 5.4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 427 AIRFOIL
       17.       17.

 0.0000000 0.0045000
 0.0125000 0.0190000
 0.0250000 0.0250000
 0.0500000 0.0360000
 0.0750000 0.0440000
 0.1000000 0.0510000
 0.1500000 0.0615000
 0.2000000 0.0695000
 0.3000000 0.0775000
 0.4000000 0.0785000
 0.5000000 0.0740000
 0.6000000 0.0670000
 0.7000000 0.0555000
 0.8000000 0.0410000
 0.9000000 0.0230000
 0.9500000 0.0120000
 1.0000000 0.0000000

 0.0000000 0.0045000
 0.0125000 0.0000000
 0.0250000 0.0005000
 0.0500000 0.0035000
 0.0750000 0.0065000
 0.1000000 0.0105000
 0.1500000 0.0175000
 0.2000000 0.0235000
 0.3000000 0.0320000
 0.4000000 0.0355000
 0.5000000 0.0330000
 0.6000000 0.0290000
 0.7000000 0.0215000
 0.8000000 0.0145000
 0.9000000 0.0070000
 0.9500000 0.0035000
 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 370 AIRFOILPreviewDetails
GOE 123 AIRFOILPreviewDetails
GOE 494 AIRFOILPreviewDetails
GOE 342 AIRFOILPreviewDetails
E63 (4.25%)PreviewDetails
GOE 483 AIRFOILPreviewDetails
S1091PreviewDetails
GOE 451 AIRFOIL (modified line 6)PreviewDetails
GOE 396 AIRFOILPreviewDetails
ARA-D 6% AIRFOILPreviewDetails

Polars for GOE 427 AIRFOIL (goe427-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe427-il50,000945.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe427-il50,000546.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe427-il100,000966.6 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe427-il100,000567.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe427-il200,000989 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe427-il200,000586.2 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe427-il500,0009114.4 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe427-il500,000594.7 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe427-il1,000,0009122.8 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe427-il1,000,000595 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit