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

GOE 505 AIRFOIL (goe505-il)

GOE 505 AIRFOIL - Gottingen 505 airfoil


Airfoil goe505-il
Details Dat file Parser  
(goe505-il) GOE 505 AIRFOIL
Gottingen 505 airfoil
Max thickness 14% at 19.7% chord.
Max camber 5.9% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 505 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0120000 0.0217800
 0.0241700 0.0360600
 0.0486500 0.0586200
 0.0732700 0.0751900
 0.0979600 0.0887500
 0.1475500 0.1063900
 0.1973000 0.1175400
 0.2971100 0.1258300
 0.3971100 0.1256300
 0.4972400 0.1199400
 0.5975000 0.1087400
 0.6979100 0.0910500
 0.7985000 0.0653700
 0.8991800 0.0356800
 0.9495900 0.0178400
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0128700 -.0162000
 0.0254700 -.0204100
 0.0505800 -.0253400
 0.0756300 -.0272600
 0.1006400 -.0276900
 0.1506000 -.0260400
 0.2005000 -.0218900
 0.3003100 -.0135900
 0.4001800 -.0078000
 0.5001800 -.0080000
 0.6002600 -.0111900
 0.7003000 -.0128900
 0.8002700 -.0115900
 0.9001600 -.0068000
 0.9501000 -.0041500
 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 510 AIRFOILPreviewDetails
GOE 534 AIRFOILPreviewDetails
GOE 512 AIRFOILPreviewDetails
Glenn Martin 2PreviewDetails
FX 73-CL1-152PreviewDetails
LNV109APreviewDetails
EPPLER 422 AIRFOILPreviewDetails
GOE 615 AIRFOILPreviewDetails
GOE 769 AIRFOILPreviewDetails
FX 73-CL2-152PreviewDetails

Polars for GOE 505 AIRFOIL (goe505-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe505-il50,000912.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe505-il50,000529.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe505-il100,000949.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe505-il100,000543.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe505-il200,000968.7 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe505-il200,000553.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe505-il500,000973.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe505-il500,000569.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe505-il1,000,000991 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe505-il1,000,000587.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit