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

GOE 133 (MVA H.11) AIRFOIL (goe133-il)

GOE 133 (MVA H.11) AIRFOIL - Gottingen 133 (MVA H.11) airfoil


Airfoil goe133-il
Details Dat file Parser  
(goe133-il) GOE 133 (MVA H.11) AIRFOIL
Gottingen 133 (MVA H.11) airfoil
Max thickness 7.9% at 30% chord.
Max camber 4.3% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 133 (MVA H.11) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0221100
 0.0250000 0.0312200
 0.0500000 0.0434500
 0.0750000 0.0526700
 0.1000000 0.0609000
 0.1500000 0.0708500
 0.2000000 0.0768000
 0.3000000 0.0827000
 0.4000000 0.0803000
 0.5000000 0.0735000
 0.6000000 0.0644000
 0.7000000 0.0523000
 0.8000000 0.0382000
 0.9000000 0.0211000
 0.9500000 0.0115500
 1.0000000 0.0020000

 0.0000000 0.0000000
 0.0125000 -.0068900
 0.0250000 -.0087700
 0.0500000 -.0081500
 0.0750000 -.0068300
 0.1000000 -.0051000
 0.1500000 -.0016500
 0.2000000 0.0008000
 0.3000000 0.0037000
 0.4000000 0.0051000
 0.5000000 0.0060000
 0.6000000 0.0064000
 0.7000000 0.0063000
 0.8000000 0.0052000
 0.9000000 0.0031000
 0.9500000 0.0015500
 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 280 (DAIMLER XI) AIRFOILPreviewDetails
GOE 408 AIRFOILPreviewDetails
GOE 315 (HANSA-BRANDENBURG III.5)PreviewDetails
GOE 328 AIRFOILPreviewDetails
GOE 277 (DAIMLER VIII) AIRFOILPreviewDetails
GOE 314 (HANSA-BRANDENBURG) AIRFOILPreviewDetails
NACA M14 AIRFOILPreviewDetails
GOE 278 (DAIMLER IX) AIRFOILPreviewDetails
GOE 178 AIRFOILPreviewDetails
GOE 122 (MVA H.2) AIRFOILPreviewDetails

Polars for GOE 133 (MVA H.11) AIRFOIL (goe133-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe133-il50,000933.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe133-il50,000540.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe133-il100,000953.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe133-il100,000558.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe133-il200,000974.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe133-il200,000574.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe133-il500,000999.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe133-il500,000593 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe133-il1,000,0009114.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe133-il1,000,0005108 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit