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

GOE 675 AIRFOIL (goe675-il)

GOE 675 AIRFOIL - Gottingen 675 airfoil


Airfoil goe675-il
Details Dat file Parser  
(goe675-il) GOE 675 AIRFOIL
Gottingen 675 airfoil
Max thickness 14.9% at 29.5% chord.
Max camber 5.9% at 39.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 675 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0114100 0.0314000
 0.0235100 0.0428200
 0.0478600 0.0616600
 0.0723600 0.0760100
 0.0969500 0.0878700
 0.1463300 0.1055900
 0.1959100 0.1178100
 0.2954900 0.1297700
 0.3954700 0.1302400
 0.4956700 0.1247200
 0.5961000 0.1122100
 0.6967800 0.0927100
 0.7977000 0.0662200
 0.8987900 0.0347300
 0.9493600 0.0184900
 1.0000000 0.0017500

 0.0000000 0.0000000
 0.0132000 -.0200400
 0.0259100 -.0261000
 0.0511200 -.0322200
 0.0761600 -.0333500
 0.1011500 -.0329900
 0.1510500 -.0302500
 0.2009400 -.0270200
 0.3006600 -.0190500
 0.4004400 -.0125800
 0.5002600 -.0076200
 0.6001400 -.0041400
 0.7000800 -.0021700
 0.8000400 -.0012000
 0.9000400 -.0012200
 0.9500500 -.0014900
 1.0000000 -.0017500
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 387 AIRFOILPreviewDetails
GOE 481A AIRFOILPreviewDetails
GOE 476 AIRFOILPreviewDetails
GOE 654 AIRFOILPreviewDetails
MH 113 14.62%PreviewDetails
GOE 711 AIRFOILPreviewDetails
WORTMANN FX 049-915 AIRFOILPreviewDetails
Glenn Martin 4PreviewDetails
GOE 567 AIRFOILPreviewDetails
FX 73-CL1-152PreviewDetails

Polars for GOE 675 AIRFOIL (goe675-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe675-il50,00098.6 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe675-il50,000528.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe675-il100,000951.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe675-il100,000552.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe675-il200,000975.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe675-il200,000569.9 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe675-il500,0009104.4 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe675-il500,000590.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe675-il1,000,0009117.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe675-il1,000,0005111.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit