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

GOE 548 AIRFOIL (goe548-il)

GOE 548 AIRFOIL - Gottingen 548 airfoil


Airfoil goe548-il
Details Dat file Parser  
(goe548-il) GOE 548 AIRFOIL
Gottingen 548 airfoil
Max thickness 11.9% at 40% chord.
Max camber 2.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 548 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0138000
 0.0250000 0.0221000
 0.0500000 0.0352000
 0.0750000 0.0433000
 0.1000000 0.0504000
 0.1500000 0.0606000
 0.2000000 0.0683000
 0.3000000 0.0787000
 0.4000000 0.0816000
 0.5000000 0.0790000
 0.6000000 0.0719000
 0.7000000 0.0595500
 0.8000000 0.0452000
 0.9000000 0.0240000
 0.9500000 0.0133000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0122000
 0.0250000 -.0174000
 0.0500000 -.0233000
 0.0750000 -.0282000
 0.1000000 -.0316000
 0.1500000 -.0364000
 0.2000000 -.0387000
 0.3000000 -.0398000
 0.4000000 -.0374000
 0.5000000 -.0330000
 0.6000000 -.0271000
 0.7000000 -.0207000
 0.8000000 -.0138000
 0.9000000 -.0069000
 0.9500000 -.0037000
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 65(1)-412PreviewDetails
LOCKHEED L-188 TIP AIRFOILPreviewDetails
NACA 63-412 AIRFOILPreviewDetails
HQ 2.5/12 AIRFOILPreviewDetails
HQ 2.0/12 AIRFOILPreviewDetails
NACA 65(1)-212 a=0.6PreviewDetails
RUTAN CANARD AIRFOILPreviewDetails
LDS-2 AIRFOILPreviewDetails
MH 120 11.57%PreviewDetails
HQ 3.0/12 AIRFOILPreviewDetails

Polars for GOE 548 AIRFOIL (goe548-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe548-il50,000934.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe548-il50,000532.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   goe548-il100,000953.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe548-il100,000551.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe548-il200,000974.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe548-il200,000568.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe548-il500,000995 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe548-il500,000576.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   goe548-il1,000,0009100.7 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe548-il1,000,000576.3 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit