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

GOE 342 AIRFOIL (goe342-il)

GOE 342 AIRFOIL - Gottingen 342 airfoil


Airfoil goe342-il
Details Dat file Parser  
(goe342-il) GOE 342 AIRFOIL
Gottingen 342 airfoil
Max thickness 5.4% at 20% chord.
Max camber 6.2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 342 AIRFOIL
       16.       16.

 0.0000000 0.0000000
 0.0125000 0.0201000
 0.0250000 0.0292000
 0.0500000 0.0414000
 0.0750000 0.0506000
 0.1000000 0.0578000
 0.1500000 0.0702000
 0.2000000 0.0786000
 0.3000000 0.0854000
 0.4000000 0.0872000
 0.5000000 0.0850000
 0.6000000 0.0778000
 0.7000000 0.0636000
 0.8000000 0.0464000
 0.9000000 0.0262000
 1.0000000 0.0030000

 0.0000000 0.0000000
 0.0125000 -.0079000
 0.0250000 -.0058000
 0.0500000 0.0004000
 0.0750000 0.0046000
 0.1000000 0.0098000
 0.1500000 0.0177000
 0.2000000 0.0246000
 0.3000000 0.0334000
 0.4000000 0.0372000
 0.5000000 0.0375000
 0.6000000 0.0358000
 0.7000000 0.0306000
 0.8000000 0.0224000
 0.9000000 0.0122000
 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 417 AIRFOILPreviewDetails
GOE 394 AIRFOILPreviewDetails
GOE 483 AIRFOILPreviewDetails
GOE 370 AIRFOILPreviewDetails
GOE 123 AIRFOILPreviewDetails
AH-7-47-6 AIRFOILPreviewDetails
GOE 427 AIRFOILPreviewDetails
GOE 803 (HACKLINGER) AIRFOILPreviewDetails
S1091PreviewDetails
E61 (5.64%)PreviewDetails

Polars for GOE 342 AIRFOIL (goe342-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe342-il50,000944.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe342-il50,000547.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe342-il100,000971.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe342-il100,000571.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe342-il200,000999.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe342-il200,000585.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   goe342-il500,0009109.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   goe342-il500,0005105.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe342-il1,000,0009130.8 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe342-il1,000,0005111.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit