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

GOE 531 AIRFOIL (goe531-il)

GOE 531 AIRFOIL - Gottingen 531 airfoil


Airfoil goe531-il
Details Dat file Parser  
(goe531-il) GOE 531 AIRFOIL
Gottingen 531 airfoil
Max thickness 13.8% at 19.5% chord.
Max camber 14.7% at 49.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 531 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0114300 0.0328700
 0.0233800 0.0497600
 0.0476400 0.0725500
 0.0720300 0.0913400
 0.0965000 0.1076400
 0.1456200 0.1347300
 0.1948900 0.1573300
 0.2938900 0.1880500
 0.3932800 0.2067800
 0.4932200 0.2085300
 0.5937700 0.1918000
 0.6949100 0.1565800
 0.7963800 0.1113800
 0.8981600 0.0566900
 0.9490800 0.0283500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0133000 -.0245700
 0.0259600 -.0296600
 0.0509500 -.0293400
 0.0757300 -.0225400
 0.1004800 -.0147300
 0.1499200 0.0023700
 0.1993200 0.0209800
 0.2982100 0.0551900
 0.3975200 0.0764200
 0.4972200 0.0856600
 0.5974200 0.0794200
 0.6980400 0.0601900
 0.7988300 0.0359600
 0.8995700 0.0132400
 0.9497899 0.0063700
 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 462 AIRFOILPreviewDetails
EPPLER 420 AIRFOILPreviewDetails
GOE 448 AIRFOILPreviewDetails
CH10 (smoothed)PreviewDetails
FX74_CL5_140PreviewDetails
FX 74-Cl5-140 MOD (smoothed)PreviewDetails
E423PreviewDetails
GOE 440 AIRFOILPreviewDetails
GOE 234 (MVA CA5) AIRFOILPreviewDetails
USA 32 AIRFOILPreviewDetails

Polars for GOE 531 AIRFOIL (goe531-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe531-il50,00094.2 at α=16.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe531-il50,00057.1 at α=18.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe531-il100,00097.7 at α=19.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe531-il100,00059.9 at α=18.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe531-il200,000913.7 at α=19.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe531-il200,000513.5 at α=17.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe531-il500,000967.5 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe531-il500,000566.1 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe531-il1,000,0009100.8 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   goe531-il1,000,000586.7 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit