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

GOE 410 AIRFOIL (goe410-il)

GOE 410 AIRFOIL - Gottingen 410 airfoil


Airfoil goe410-il
Details Dat file Parser  
(goe410-il) GOE 410 AIRFOIL
Gottingen 410 airfoil
Max thickness 16.1% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 410 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0260000
 0.0250000 0.0365000
 0.0500000 0.0505000
 0.0750000 0.0590000
 0.1000000 0.0650000
 0.1500000 0.0725000
 0.2000000 0.0780000
 0.3000000 0.0805000
 0.4000000 0.0745000
 0.5000000 0.0630000
 0.6000000 0.0500000
 0.7000000 0.0360000
 0.8000000 0.0220000
 0.9000000 0.0100000
 0.9500000 0.0045000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0260000
 0.0250000 -.0365000
 0.0500000 -.0505000
 0.0750000 -.0590000
 0.1000000 -.0650000
 0.1500000 -.0725000
 0.2000000 -.0780000
 0.3000000 -.0805000
 0.4000000 -.0745000
 0.5000000 -.0630000
 0.6000000 -.0500000
 0.7000000 -.0360000
 0.8000000 -.0220000
 0.9000000 -.0100000
 0.9500000 -.0045000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 479 AIRFOILPreviewDetails
S1046 17% (Danny Howell)PreviewDetails
WORTMANN FX L V-152 AIRFOILPreviewDetails
EPPLER E837 HYDROFOIL AIRFOILPreviewDetails
NACA 0015PreviewDetails
FX 71-L-150/20 AIRFOILPreviewDetails
FX 71-L-150/25 AIRFOILPreviewDetails
FX 71-L-150/30 AIRFOILPreviewDetails
FX 71-L-150/30 AIRFOILPreviewDetails
EPPLER 473 AIRFOILPreviewDetails

Polars for GOE 410 AIRFOIL (goe410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe410-il50,000920.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe410-il50,000525.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe410-il100,000937.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe410-il100,000535.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe410-il200,000946.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe410-il200,000545.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe410-il500,000962.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe410-il500,000565.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe410-il1,000,000982 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe410-il1,000,000581.8 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit