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

GOE 55 AIRFOIL (goe55-il)

GOE 55 AIRFOIL - Gottingen 55 airfoil


Airfoil goe55-il
Details Dat file Parser  
(goe55-il) GOE 55 AIRFOIL
Gottingen 55 airfoil
Max thickness 6.2% at 14.9% chord.
Max camber 2% at 19.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 55 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0122300 0.0197700
 0.0246500 0.0257400
 0.0495200 0.0345800
 0.0744400 0.0406200
 0.0993900 0.0443700
 0.1493300 0.0490500
 0.1993000 0.0509400
 0.2993700 0.0460200
 0.3994600 0.0393900
 0.4995500 0.0335600
 0.5996200 0.0278400
 0.6997000 0.0218200
 0.7997700 0.0164000
 0.8998500 0.0101800
 0.9499000 0.0069600
 1.0000000 0.0037500

 0.0000000 0.0000000
 0.0126800 -.0133300
 0.0252200 -.0160500
 0.0502300 -.0168100
 0.0752200 -.0161700
 0.1002000 -.0144200
 0.1501700 -.0125400
 0.2001400 -.0101500
 0.3000900 -.0068700
 0.4000600 -.0045000
 0.5000400 -.0031200
 0.6000200 -.0017500
 0.7000100 -.0009700
 0.8000100 -.0008000
 0.9000200 -.0017200
 0.9500400 -.0027400
 1.0000000 -.0037500
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 66-H-60PreviewDetails
RAF 15 AIRFOILPreviewDetails
HT23PreviewDetails
GOE 54 AIRFOILPreviewDetails
HT22PreviewDetails
PW1211PreviewDetails
AG455ct -02f rot.PreviewDetails
AG46ct -02f rot.PreviewDetails
AG45c -03fPreviewDetails
AG11PreviewDetails

Polars for GOE 55 AIRFOIL (goe55-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe55-il50,000926.3 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   goe55-il50,000532.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe55-il100,000942.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe55-il100,000543.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe55-il200,000954.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe55-il200,000551.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe55-il500,000964.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe55-il500,000564.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe55-il1,000,000972.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe55-il1,000,000577.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit