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

GOE 122 (MVA H.2) AIRFOIL (goe122-il)

GOE 122 (MVA H.2) AIRFOIL - Gottingen 122 (MVA H.2) airfoil


Airfoil goe122-il
Details Dat file Parser  
(goe122-il) GOE 122 (MVA H.2) AIRFOIL
Gottingen 122 (MVA H.2) airfoil
Max thickness 7.3% at 30% chord.
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 122 (MVA H.2) AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0123800 0.0183800
 0.0248300 0.0256600
 0.0497600 0.0379200
 0.0746900 0.0480800
 0.0996400 0.0559400
 0.1495800 0.0656600
 0.1995300 0.0725900
 0.2995000 0.0771300
 0.3995300 0.0738800
 0.4995700 0.0673200
 0.5996300 0.0569700
 0.6997100 0.0449100
 0.7998000 0.0306600
 0.8999000 0.0152000
 0.9499500 0.0083300
 1.0000000 0.0012500

 0.0000000 0.0000000
 0.0125500 -.0076200
 0.0250500 -.0075400
 0.0500400 -.0067800
 0.0750400 -.0055200
 0.1000300 -.0042500
 0.1500200 -.0023300
 0.2000000 -.0003100
 0.2999700 0.0041300
 0.3999600 0.0059800
 0.4999600 0.0066200
 0.5999600 0.0055700
 0.6999800 0.0034100
 0.7999800 0.0015700
 0.9000000 -.0001900
 0.9500100 -.0009700
 1.0000000 -.0012500
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 276 (DAIMLER VII) AIRFOILPreviewDetails
GOE 278 (DAIMLER IX) AIRFOILPreviewDetails
GOE 101 AIRFOILPreviewDetails
GOE 408 AIRFOILPreviewDetails
I.S.A. 571PreviewDetails
GOE 133 (MVA H.11) AIRFOILPreviewDetails
GOE 280 (DAIMLER XI) AIRFOILPreviewDetails
GOE 315 (HANSA-BRANDENBURG III.5)PreviewDetails
NACA M14 AIRFOILPreviewDetails
GOE 401 AIRFOILPreviewDetails

Polars for GOE 122 (MVA H.2) AIRFOIL (goe122-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe122-il50,000937.6 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe122-il50,000539.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe122-il100,000955.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe122-il100,000556.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe122-il200,000973.3 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe122-il200,000572.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe122-il500,000995.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe122-il500,000589.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe122-il1,000,0009110.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe122-il1,000,000597.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit