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

GOE 435 AIRFOIL (goe435-il)

GOE 435 AIRFOIL - Gottingen 435 airfoil


Airfoil goe435-il
Details Dat file Parser  
(goe435-il) GOE 435 AIRFOIL
Gottingen 435 airfoil
Max thickness 26.1% at 27.8% chord.
Max camber 4.7% at 48% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 435 AIRFOIL
       17.       17.

 0.0000700 0.0000000
 0.0075500 0.0381800
 0.0177600 0.0555200
 0.0393100 0.0817600
 0.0618900 0.1001300
 0.0847400 0.1164400
 0.1316800 0.1396200
 0.1797900 0.1539500
 0.2780800 0.1668900
 0.3780900 0.1667600
 0.4798200 0.1535500
 0.5825100 0.1330700
 0.6863800 0.1036500
 0.7906600 0.0710800
 0.8952100 0.0364500
 0.9475901 0.0183500
 1.0000000 0.0013500

 0.0000700 0.0000000
 0.0177300 -.0391700
 0.0322200 -.0542600
 0.0592000 -.0693100
 0.0856300 -.0809300
 0.1122300 -.0904300
 0.1626500 -.0955900
 0.2128300 -.0969800
 0.3121500 -.0919100
 0.4098200 -.0742500
 0.5072800 -.0550200
 0.6047400 -.0357900
 0.7023400 -.0176400
 0.8003600 -.0026300
 0.8996900 0.0024400
 0.9498700 0.0010500
 1.0000000 -.0013500
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

WORTMANN FX 77-W-258 AIRFOILPreviewDetails
MH 150 23.89%PreviewDetails
FX 69-PR-281PreviewDetails
NACA 4424PreviewDetails
WORTMANN FX 69-274PreviewDetails
FX 77-W-270PreviewDetails
FX 77-W-270SPreviewDetails
TH 25816 HALE AIRFOILPreviewDetails
SIKORSKY DBLN-526 AIRFOILPreviewDetails
RAF 89 AIRFOILPreviewDetails

Polars for GOE 435 AIRFOIL (goe435-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe435-il50,00092.8 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe435-il50,00057.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe435-il100,000925.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe435-il100,000533.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe435-il200,000952.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe435-il200,000550.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe435-il500,000975.8 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe435-il500,000569.9 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe435-il1,000,000995.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe435-il1,000,000579.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit