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

GOE 412 AIRFOIL (goe412-il)

GOE 412 AIRFOIL - Gottingen 412 airfoil


Airfoil goe412-il
Details Dat file Parser  
(goe412-il) GOE 412 AIRFOIL
Gottingen 412 airfoil
Max thickness 13.1% at 29.7% chord.
Max camber 5.1% at 39.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 412 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0118800 0.0222300
 0.0240600 0.0338700
 0.0485900 0.0509500
 0.0732400 0.0634300
 0.0979300 0.0747100
 0.1475200 0.0894900
 0.1972200 0.1004600
 0.2968700 0.1128200
 0.3967800 0.1160900
 0.4969200 0.1113600
 0.5972500 0.0992400
 0.6977600 0.0807300
 0.7984000 0.0579200
 0.8991200 0.0319100
 0.9495500 0.0162000
 1.0000000 0.0016000

 0.0000000 0.0000000
 0.0129500 -.0161400
 0.0255600 -.0200900
 0.0506800 -.0247000
 0.0757200 -.0261000
 0.1007300 -.0265100
 0.1507000 -.0251300
 0.2006600 -.0237400
 0.3005100 -.0182800
 0.4003900 -.0139100
 0.5002900 -.0104400
 0.6002000 -.0073700
 0.7001700 -.0062100
 0.8001200 -.0044400
 0.9001100 -.0038700
 0.9500800 -.0029800
 1.0000000 -.0016000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

USA 27 mod. AIRFOILPreviewDetails
USA 29 AIRFOILPreviewDetails
GOE 584 AIRFOILPreviewDetails
GOE 414 AIRFOILPreviewDetails
Dayton-Wright 6PreviewDetails
GOE 701 AIRFOILPreviewDetails
GOE 532 AIRFOILPreviewDetails
GOE 426 AIRFOILPreviewDetails
GOE 553 AIRFOILPreviewDetails
GOE 533 AIRFOILPreviewDetails

Polars for GOE 412 AIRFOIL (goe412-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe412-il50,000915.9 at α=15.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe412-il50,000526.8 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   goe412-il100,000954.7 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe412-il100,000555.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe412-il200,000982.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe412-il200,000579.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe412-il500,0009116.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe412-il500,0005103.2 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe412-il1,000,0009137.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe412-il1,000,0005113.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit